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Aerodynamics, Transonic

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Aerodynamics of transonic flight
Transonic aerodynamics
Transonic speeds
Trans-sonic aerodynamics

Filed under: Aerodynamics, Transonic

High speed aerodynamics and jet propulsion (Princeton University Press, 1955) (page images at HathiTrust)
Unsteady transonic flow. (Pergamon Press, 1961), by Mårten Landahl (page images at HathiTrust)
Experiments in transonic flow (Wright Field, Dayton, Ohio : Headquarters, Wright Patterson Air Force Base, 1948., 1948), by Jean G. Goppert, Joseph Flatt, United States. Air Force. Air Matériel Command, and California Institute of Technology (page images at HathiTrust)
Effects of afterbody boattail design and empennage arrangement on aeropropulsive characteristics of a twin-engine fighter model at transonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1987), by Linda S. Bangert, David E. Reubush, Laurence D. Leavitt, and Langley Research Center (page images at HathiTrust)
Calculation of viscous effects on transonic flow for oscillating airfoils and comparisons with experiment (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by James T. Howlett, Samuel R. Bland, and Langley Research Center (page images at HathiTrust)
Effect of empennage arrangement on single-engine nozzle/afterbody static pressures at transonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1987), by William P. Henderson, James R. Burley, and Langley Research Center (page images at HathiTrust)
The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : design overview (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by Charles D. Harris, Cuyler W. Brooks, William D. Harvey, and Langley Research Center (page images at HathiTrust)
Integration effects of pylon geometry on a high-wing transport plane (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by John R. Carlson, Milton Lamb, and United States. National Aeronautics and Space Administration. Office of Management (page images at HathiTrust)
NASA supercritical airfoils : a matrix of family-related airfoils (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Charles D. Harris and Langley Research Center (page images at HathiTrust)
Theoretical and experimental engine-inlet flow fields for fighter forebodies (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Steven F. Yaros and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Aerodynamic design for improved maneuverability by use of three-dimensional transonic theory (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Michael J. Mann, James C. Ferris, Richard L. Campbell, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Transonic and supersonic Euler computations of vortex-dominated flow fields about a generic fighter (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Aga M. Goodsell, John E. Melton, and Ames Research Center (page images at HathiTrust)
Planform curvature effects on flutter characteristics of a wing with 56 ̊leading-edge sweep and panel aspect ratio of 1.14 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Donald F. Keller, Theresa L. Pinkerton, M. C. Sandford, and Langley Research Center (page images at HathiTrust)
Wind tunnel investigation of vortex flows on F/A-18 configuration at subsonic through transonic speeds (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Gary E. Erickson and Langley Research Center (page images at HathiTrust)
Effects of yaw angle and Reynolds number on rectangular-box cavities at subsonic and transonic speeds (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Elizabeth B. Plentovich, M. B. Tracy, and Julio Chu (page images at HathiTrust)
Wall-interference assessment and corrections for transonic NACA 0012 airfoil data from various wind tunnels (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Lawrence L. Green, Perry A. Newman, and Langley Research Center (page images at HathiTrust)
A method for the design of transonic flexible wings (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Leigh Ann Smith, Richard L. Campbell, and Langley Research Center (page images at HathiTrust)
Fuselage and nozzle pressure distributions on a 1/12-scale F-15 propulsion model at transonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Odis C. Pendergraft, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Experimental and analytical transonic flutter characteristics of a geared-elevator configuration (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Charles L. Ruhlin, Richard A. Gregory, Robert V. Doggett, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Transonic aerodynamic characteristics of a tailless fixed-wing supersonic transport model (National Aeronautics and Space Administration ;, 1966), by Edward J. Ray, Robert T. Taylor, and Langley Research Center (page images at HathiTrust)
The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : suction coefficient analysis (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Cuyler W. Brooks, William D. Harvey, Charles D. Harris, and Langley Research Center (page images at HathiTrust)
Flight Reynolds number effects on a contoured boattail nozzle at subsonic speeds (National Aeronautics and Space Administration ;, 1974), by Roger Chamberlin and Lewis Research Center (page images at HathiTrust)
Measurements of fluctuating pressure in a rectangular cavity in transonic flow at high Reynolds numbers (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by M. B. Tracy, Julio Chu, Elizabeth B. Plentovich, and Langley Research Center (page images at HathiTrust)
Transonic flow analysis for rotors. Part 3, Three-dimensional, quasi-steady, Euler calculation (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by I-Chung Chang and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
Aerodynamic design of the contoured wind-tunnel liner for the NASA supercritical, laminar-flow-control, swept-wing experiment (National Information Branch ;, 1984), by Perry A. Newman, John B. Peterson, E. Clay Anderson, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Fuselage and nozzle pressure distributions of a 1/12-scale f-15 propulsion model at transonic speeds effect of fuselage modifications and nozzle variables (National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1984), by Odis C. Pendergraft, George T. Carson, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Use of CYBER 203 and CYBER 205 computers for three-dimensional transonic flow calculations (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by N. Duane Melson, James D. Keller, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Influence of orbital-maneuvering-system fairings and rudder flare on the transonic aerodynamic characteristics of a space shuttle orbiter (National Aeronautics and Space Administration ;, 1975), by James C. Ellison and Langley Research Center (page images at HathiTrust)
Forward-swept-wing configuration designed for high maneuverability by use of a transonic computational method (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Michael J. Mann, Charles E. Mercer, and Langley Research Center (page images at HathiTrust)
Comparison of wind tunnel and flight test afterbody and nozzle pressures for a twin-jet fighter aircraft at transonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1987), by Jack Nugent, Odis C. Pendergraft, and Ames Research Center (page images at HathiTrust)
Effect of nacelles on aerodynamic characteristics of an executive-jet model with simulated, partial-chord, laminar-flow-control wing glove (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Richard L. Campbell, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Effects of reset stators and a rotating, grooved stator hub on performance of a 1.92-pressure-ratio compressor stage (National Aeronautics and Space Administration ;, 1977), by George W. Lewis, Lonnie Reid, Donald C. Urasek, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Effect of casing treatment on overall performance of axial-flow transonic fan stage with pressure ratio of 1.75 and tip solidity of 1.5 (National Aeronautics and Space Administration ;, 1977), by Walter M. Osborn, Royce D. Moore, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A simple method for converting frequency-domain aerodynamics to the time domain (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by E. H. Dowell and Langley Research Center (page images at HathiTrust)
A potential-flow/boundary layer method for calculating subsonic and transonic airfoil flow with trailing-edge separation (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Richard W. Barnwell, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Effects of tip clearance on overall performance of transonic fan stage with and without casing treatment (National Aeronautics and Space Administration ;, 1977), by Royce D. Moore, Walter Martin Osborn, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Plenum response to simulated disturbances of the model and fan inlet guide vanes in a transonic tunne (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Blair B. Gloss and Langley Research Center (page images at HathiTrust)
Static and dynamic pressure measurements on a NACA 0012 airfoil in the Ames High Reynolds Number Facility (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by John B. McDevitt, Arthur F. Okuno, and Ames Research Center (page images at HathiTrust)
Transonic off-design drag and performance of an axisymmetric inlet with 40 percent internal contraction on design (National Aeronautics and Space Administration ;, 1974), by Richard R. Woollett, David A. Choby, Edward T. Meleason, and Lewis Research Center (page images at HathiTrust)
Design and performance of a high-pressure-ratio, highly loaded axial-flow transonic compressor space (National Aeronautics and Space Administration ;, 1974), by George W. Lewis, Edward R. Tysl, Lonnie Reid, and Lewis Research Center (page images at HathiTrust)
Flight Reynolds number effects on a fighter-type, circular-arc - 19 ̊conic boattail nozzle at subsonic speeds (National Aeronautics and Space Administration ;, 1974), by Roger Chamberlin and Lewis Research Center (page images at HathiTrust)
Transonic off-design drag and performance of three mixed-compression axisymmetric inlets (National Aeronautics and Space Administration ;, 1975), by Richard R. Woollett, David A. Choby, Edward T. Meleason, and Lewis Research Center (page images at HathiTrust)
The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : evaluation of initial perforated configuration (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Charles D. Harris and Langley Research Center (page images at HathiTrust)
Performance of inlet stage of transonic compressor (National Aeronautics and Space Administration ;, 1976), by Donald C. Urasek, George W. Lewis, Ronald J. Steinke, and Lewis Research Center (page images at HathiTrust)
Numerical study of transonic flow over oscillating airfoils using the full potential equation (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Koji Isogai and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Two dimensional transonic testing with splitter plates (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Sanford Davis, Bodapati Satyanarayana, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Computation of transonic boattail flow with separation (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Richard G. Wilmoth and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Jet exhaust and support interference effects on the transonic aerodynamic characteristics of a fighter model with two widely spaced engines (National Aeronautics and Space Administration ;, 1976), by William B. Compton and United States National Aeronautics and Space Administration (page images at HathiTrust)
Close-range photogrammetric measurement of static deflections for an aeroelastic superficial wing (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Thomas A. Byrdsong, M. C. Sandford, Richard R. Adams, and Langley Research Center (page images at HathiTrust)
Transonic Navier-Stokes solutions of three-dimensional afterbody flows (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by William B. Compton and Langley Research Center (page images at HathiTrust)
Transonic aerodynamic characteristics of a proposed assured crew return capability (ACRC) lifting-body configuration (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by George M. Ware and Langley Research Center (page images at HathiTrust)
Detailed transonic flow field measurements about a supercritical airfoil section (National Aeronautics and Space Administration ;, 1975), by Francis X. Hurley and Ames Research Center (page images at HathiTrust)
Integration of aft-fuselage-mounted flow-through engine nacelles on an advanced transport configuration at Mach numbers from 0.6 to 1.0 (National Aeronautics and Space Administration ;, 1975), by Bernard J. Blaha and Lewis Research Center (page images at HathiTrust)
Theoretical estimation of the transonic aerodynamic characteristics of a supercritical-wing transport model with trailing-edge controls (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by James M. Luckring, Michael J. Mann, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Longitudinal aerodynamic characteristics of a generic fighter model with a wing designed for sustained transonic maneuver conditions (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by James C. Ferris and Langley Research Center (page images at HathiTrust)
Pressure distributions from high Reynolds number tests of a Boeing BAC I airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William G. Johnson, Acquilla S. Hill, and Langley Research Center (page images at HathiTrust)
Performance characteristics of an isolated coannular plug nozzle at transonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Charles E. Mercer, James R. Burley, and Langley Research Center (page images at HathiTrust)
Effects of airfoil shape, thickness, camber, and angle of attack on calculated transonic unsteady airloads (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by John T. Batina and Langley Research Center (page images at HathiTrust)
Investigation of a supersonic cruise fighter model flow field (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by David E. Reubush, E. Ann Bare, and Langley Research Center (page images at HathiTrust)
Theoretical and experimental flow fields for a supersonic cruise fighter forebody (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Steven F. Yaros and Langley Research Center (page images at HathiTrust)
Supercritical maneuvering fighter configuration : wind-tunnel investigation at Mach numbers of 0.60 to 0.95 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Michael J. Mann, Richard L. Campbell, Charles E. Mercer, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
The design of supercritical wings by the use of three-dimensional transonic theory (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Michael J. Mann and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
A fan pressure ratio correlation in terms of Mach number and Reynolds number for the Langley 0.3-meter transonic cryogenic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Pierce L. Lawing, Charles L. Ladson, Jerry B. Adcock, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William G. Johnson, Otto Eichmann, Acquilla S. Hill, and Langley Research Center (page images at HathiTrust)
High Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William G. Johnson, Otto Eichmann, Acquilla S. Hill, and Langley Research Center (page images at HathiTrust)
Navier-Stokes analysis of transonic cascade flow (National Aeronautics and Space Administration ;, 1990), by A. Arnone, Louis A. Povinelli, M. S. Liou, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Experimental study of wing leading-edge devices for improved maneuver performance of a supercritical maneuvering fighter configuration (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Michael J. Mann and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Numerical computation of shock wave : turbulent boundary layer interaction in transonic flow over an axisymmetric curved hill (National Aeronautics and Space Administration ;, 1989), by S.-W. Kim and United States National Aeronautics and Space Administration (page images at HathiTrust)
Improved method for calculating transonic velocities on blade-to-blade stream surfaces of a turbomachine (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Jerry R. Wood, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Lewis Research Center (page images at HathiTrust)
Computer program for calculating full potential transonic, quasi-three-dimensional flow through a rotating turbomachinery blade row (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Charles A. Farrell, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
A method for modifying two-dimensional adaptive wind-tunnel walls including analytical and experimental verification (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Joel L. Everhart and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Effect of tail size reductions on longitudinal aerodynamic characteristics of a three-surface F-15 model with nonaxisymmetric nozzles (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Mark C. Frassinelli, George T. Carson, and Langley Research Center (page images at HathiTrust)
CAS22 - FORTRAN program for fast design and analysis of sock-free airfoil cascades using fictitious-gas concept (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by George S. Dulikravich, Helmut Sobieczy, Universities Space Research Association, DFVLR--Institute fur̈ Theoretische Strom̈ungsmechanik, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Lewis Research Center (page images at HathiTrust)
High Reynolds number flows (National Aeronautics and Space Administration ;, 1971), by David A. Russell, United States National Aeronautics and Space Administration, and University of Washington (page images at HathiTrust)
High Reynolds number tests of a C141A aircraft semispan model to investigate shock-induced separation (National Aeronautics and Space Administration ;, 1975), by W. T. Blackerby, J. F. Cahill, Ames Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
Linear aerodynamic loads on cone-cylinders at Mach numbers from 0.7 to 2.0 (National Aeronautics and Space Administration, 1966), by Roger Lee Hamner and Alan D. Leff (page images at HathiTrust)
Evaluation of structural design concepts for an arrow-wing supersonic cruise aircraft (National Aeronautics and Space Administration ;, 1977), by I. F. Sakata, G. W. Davis, Lockheed-California Company, and United States National Aeronautics and Space Administration (page images at HathiTrust)
The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : drag euqations (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Cuyler W. Brooks, William D. Harvey, and Charles D. Harris (page images at HathiTrust)
Investigation of Northrop F-5A wing buffet intensity in transonic flight (National Aeronautics and Space Administration ;, 1974), by Chintsun Hwang, W. S. Pi, Ames Research Center, and Northrop Corporation. Aircraft Division (page images at HathiTrust)
High-transonic-speed transport aircraft study : summary report (National Aeronautics and Space Administration ;, 1974), by Robert M. Kulfan, Ames Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
High Reynolds number test of a NACA 65₁-213, a = 0.5 airfoil at transonic speeds (National Aeronautics and Space Administration ;, 1975), by Kenneth P. Burdges, Gerald A. Pounds, James A. Blackwell, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
Transonic performance of a Mach 2.65 auxiliary flow axisymmetric inlet (National Aeronautics and Space Administration ;, 1976), by Don M. Santman, United States National Aeronautics and Space Administration, Ames Research Center, and Inc Ellco Engineering (page images at HathiTrust)
Steady inviscid transonic flows over planar airfoils : a search for a simplified procedure (National Aeronautics and Space Administration ;, 1973), by R. Magnus, H. Yoshihara, Ames Research Center, and General Dynamics Corporation. Convair Division (page images at HathiTrust)
Feasibility of combining linear theory and impact theory methods for the analysis and design of high speed configurations (National Aeronautics and Space Administration, Scientific and Technical Information Service ;, 1979), by D. Brooke, D. V. Vondrasek, Langley Research Center, McDonnell Douglas Corporation, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Numerical computation of transonic flows by finite-element and finite-diffence methods (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, M. M. Hafez, Langley Research Center, and inc Flow Research (page images at HathiTrust)
Analytical method for predicting the pressure distribution about a nacelle at transonic speeds (National Aeronautics and Space Administration ;, 1973), by J. S. Keith, Langley Research Center, and General Electric Company (page images at HathiTrust)
Finite element analysis of transonic flows in cascades : importance of computational grids in improving accuracy and convergence (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Akin Ecer, Hasan U. Akay, IUPUI (Campus), United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Lewis Research Center (page images at HathiTrust)
High angle canard missile test in the Ames 11-foot transonic wind tunnel (National Aeronautics and Space Adiministration, Scientific and Technical Information Office ;, 1978), by Richard G. Schwind and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Operational manual for two-dimensional transonic code TSFOIL (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Stephen S. Stahara, Ames Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Nielsen Engineering & Research (page images at HathiTrust)
Perturbation solutions for transonic flow on the blade-to-blade surface of compressor blade rows (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Stephen S. Stahara, John R. Spreiter, D. S. Chaussee, Inc Neilsen Engineering and Research, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
TAS--a transonic aircraft/store flow field prediction code (The Center :, 1983), by D. S. Thompson, General Dynamics Corporation. Fort Worth Division, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Ames Research Center (page images at HathiTrust)
Development of a multiple-parameter nonlinear perturbation procedure for transonic turbomachinery flows : preliminary application to design/optimization problems (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Stephen S. Stahara, John R. Spreiter, J. P. Elliott, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Transonic pressure measurements and comparison of theory to experiment for three arrow-wing configurations : summary report (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Marjorie E. Manro, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Three-dimensional transonic potential flow about complex three-dimensional configurations (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Theodore A. Reyhner, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Boeing Commercial Airplane Company, and Langley Research Center (page images at HathiTrust)
A study of the effects of Reynolds number and mach number on constant pressure coefficient jump for shock-induced trailing-edge separation (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Atlee M. Cunningham and Gregory S. Spragle (page images at HathiTrust)
Correlation of data related to shock-induced trailing-edge separation and extrapolation to flight Reynolds number (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by J. F. Cahill, P. C. Connor, Ames Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
A direct-inverse method for transonic and separated flows about airfoils (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Leland A. Carlson, Langley Research Center, and Texas A & M University. Aerospace Engineering Dept (page images at HathiTrust)
Theoretical/numerical study of feasibility of use of winglets on low aspect ratio wings at subsonic and transonic Mach numbers to reduce drag (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by John Kuhlmann, Michael J. Cerney, Paul Liaw, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
Numerical simulation and comparison of symmetrical/supercritical airfoils for the near tip region of a helicopter in forward flight (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1989), by F. F. Badavi and Langley Research Center (page images at HathiTrust)
Method to predict external store carriage characteristics at transonic speeds / Bruce S. Rosen. (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by Bruce S. Rosen and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
A linear aerodynamic analysis for unsteady transonic cascades (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Joseph M. Verdon, Joseph R. Caspar, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Lewis Research Center (page images at HathiTrust)
Transonic aeroelastic analysis of launch vehicle configurations (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by João Luiz Filgueiras de Azevedo and Langley Research Center (page images at HathiTrust)
Theoretical pressure distributions on wings of finite span at zero incidence for mach numbers near 1 (U.S. G.P.O., 1961), by Alberta Y. Alksne, John R. Spreiter, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Effects of jet exhaust gas properties on exhaust simulation and afterbody drag (National Aeronautics and Space Administration ;, 1975), by William B. Compton and Langley Research Center (page images at HathiTrust)
NASA TN D-1982 (National Aeronautics and Space Administration, 1963), by Henry A. Cole, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Variants and extensions of a fast direct numerical Cauchy-Riemann solver, with illustrative applications (Natural Aeronautics and Space Administration :, 1977), by E. Dale Martin, Harvard Lomax, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-2360 (National Aeronautics and Space Administration :, 1964), by Robert C. Goetz, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Afterbody pressures on 2-dimensional boattailed bodies having turbulent boundary layers at Mach 5.98 (National Aeronautics and Space Administration :, 1964), by W. Frank Staylor, Theodore J. Goldberg, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Some observations of the effects of radial distortions on performance of a transonic rotating blade row (National Aeronautics and Space Administration ;, 1974), by Donald M. Sandercock, Nelson L. Sanger, and Lewis Research Center (page images at HathiTrust)
Shadowgraph study of the upper stage flow fields of some Saturn V study configurations in the transonic Mach number range (National Aeronautics and Space Administration ;, 1965), by C. Dale Andrews, David R. Carlson, and George C. Marshall Space Flight Center (page images at HathiTrust)
Transonic aerodynamic characteristics of several bodies having elliptical cross sections and various plan forms (National Aeronautics and Space Administration, 1959), by Robert A. Taylor and Ames Research Center (page images at HathiTrust)
A transonic investigation of base pressures associated with shallow three-dimensional rearward-facing steps (National Aeronautics and Space Administration ;, 1965), by Thomas C. Kelly and Langley Research Center (page images at HathiTrust)
Calculation of the twist distribution of wings designed for cruise at transonic speeds (National Aeronautics and Space Administration ;, 1974), by Michael J. Mann and Langley Research Center (page images at HathiTrust)
Some observations about the components of transonic fan noise from narrow-band spectral analysis (National Aeronautics and Space Administration ;, 1974), by Arthur V. Saule and Lewis Research Center (page images at HathiTrust)
Experimental investigation of the influence of the turbulent boundary layer on the pressure distribution over a rigid two-dimensional wavy wall (National Aeronautics and Space Administration ;, 1971), by Lado Muhlstein, Richard G. Beranek, George C. Marshall Space Flight Center, and Ames Research Center (page images at HathiTrust)
Experimental parametric studies of transonic T-tail flutter (National Aeronautics and Space Administration ;, 1975), by Charles L. Ruhlin, M. C. Sandford, and Langley Research Center (page images at HathiTrust)
FORTRAN program for quasi-three-dimensional calculation of surface velocities and choking flow for turbomachine blade rows (National Aeronautics and Space Administration ;, 1971), by Theodore Katsanis (page images at HathiTrust)
Effect of nonlifting empennage surfaces on single-engine afterbody/nozzle drag at Mach numbers from 0.5 to 2.2 (National Aeronautics and Space Administration ;, 1977), by Bobby L. Berrier and United States National Aeronautics and Space Administration (page images at HathiTrust)
Numerical calculation of transonic boattail flow (National Aeronautics and Space Administration ;, 1975), by Wen L. Chow, Bernhard H. Anderson, Lawrence J. Bober, and Lewis Research Center (page images at HathiTrust)
The effects on propulsion-induced aerodynamic forces of vectoring a partial-span rectangular jet at Mach numbers from 0.40 to 1.20 (National Aeronautics and Space Administration ;, 1975), by Francis J. Capone and Langley Research Center (page images at HathiTrust)
Performance of a 1.57-pressure-ratio transonic fan stage with a screen-induced 90 ̊circumferential inlet flow distribution (National Aeronautics and Space Administration ;, 1976), by Nelson L. Sanger and Lewis Research Center (page images at HathiTrust)
Some anomalies observed in wind-tunnel tests of a blunt body at transonic and supersonic speeds (National Aeronautics and Space Administration ;, 1976), by Joseph D. Brooks, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Wind-tunnel tests of modified cross, hemisflo, and disk-gap-band parachutes with emphasis in the transonic range (National Aeronautics and Space Administration ;, 1974), by James T. Foughner, William C. Alexander, and Langley Research Center (page images at HathiTrust)
Extraction from flight data of lateral aerodynamic coefficients for F-8 aircraft with supercritical wing (National Aeronautics and Space Administration ;, 1974), by James L. Williams, William T. Suit, and Langley Research Center (page images at HathiTrust)
FORTRAN program for calculating transonic velocities on a blade-to-blade stream surface of a turbomachine (National Aeronautics and Space Administration ;, 1969), by Theodore Katsanis, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
FORTRAN program for calculating velocities and streamlines on a blade-to-blade stream surface of a tandem blade turbomachine (National Aeronautics and Space Administration ;, 1969), by Theodore Katsanis, William D. McNally, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-5655 (National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Charles E. Mercer, Bobby L. Berrier, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
NASA TN D-5538 (National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Irving Abel, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-5713 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Howard Tashjian, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Hypersonic and transonic buzz measurements on the lower pitch flap of M2-F2 lifting entry configuration (National Aeronautics and Space Administration ;, 1972), by Robert W. Warner, Phillip R. Wilcox, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Computer program for definition of transonic axial flow compressor blade rows (National Aeronautics and Space Administration ;, 1974), by James E. Crouse and Lewis Research Center (page images at HathiTrust)
Transonic single-mode flutter and buffet of a low aspect ratio wing having a subsonic airfoil shape (National Aeronautics and Space Administration ;, 1974), by Larry L. Erickson, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Extraction from flight data of longitudinal aerodynamic coefficients for F-8 aircraft with supercritical wing (National Aeronautics and Space Administration ;, 1974), by James L. Williams, William T. Suit, and Langley Research Center (page images at HathiTrust)
Experimental investigation of the transonic flutter of simple thin truncated-cone panels (National Aeronautics and Space Administration, 1961), by Jean Gilman and Langley Research Center (page images at HathiTrust)
Static longitudinal aerodynamic characteristics at transonic speeds and angles of attack up to 99 degree of a reentry glider having folding wing-tip panels (National Aeronautics and Space Administration, 1961), by Walter B. Olstad and Langley Research Center (page images at HathiTrust)
Transonic and supersonic flutter trend investigation of a variable-sweep wing (National Aeronautics and Space Administration, 1961), by John C. Stonesifer, Robert C. Goetz, and Langley Research Center (page images at HathiTrust)
Drag of a supercritical body of revolution in free flight at transonic speeds and comparison with wind-tunnel data (National Aeronautics and Space Administration ;, 1971), by J. W. Usry, John W. Wallace, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Performance of a transonic compressor rotor with an aspect ratio of 6.5 (National Aeronautics and Space Administration ;, 1974), by Lonnie Reid, Edward R. Tysl, and Lewis Research Center (page images at HathiTrust)
NASA TN D-3701 (National Aeronautics and Space Administration :, 1966), by James C. Ferris and United States National Aeronautics and Space Administration (page images at HathiTrust)
An investigation of transonic flow fields surrounding hot and cold sonic jets (National Aeronautics and Space Administration, 1961), by George Lee and Ames Research Center (page images at HathiTrust)
Investigation at transonic speeds of loading over a 30 deg sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section mounted on a body (National Aeronautics and Space Administration :, 1960), by Donald D. Arabian and United States National Aeronautics and Space Administration (page images at HathiTrust)
Experimental investigation at transonic speeds of pressure distributions over wedge and circular-arc airfoil sections and evaluation of perforated-wall interference (National Aeronautics and Space Administration, 1959), by Earl D. Knechtel and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-1961 (National Aeronautics and Space Administration, 1963), by Albin O. Pearson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
NASA TN D-1966 (National Aeronautics and Space Administration, 1963), by E. Carson Yates, Annie G. Fox, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Effects of increased leading-edge thickness on performance of a transonic rotor blade (National Aeronautics and Space Administration ;, 1973), by Lonnie Reid, Donald C. Urasek, and Lewis Research Center (page images at HathiTrust)
Transonic wind-tunnel investigation of the static aerodynamic characteristics of several configurations of the Blue Scout launch vehicle (National Aeronautics and Space Administration, 1963), by Thomas C. Kelly, Robert J. Keynton, and Langley Research Center (page images at HathiTrust)
Effect of blockage ratio on drag and pressure distributions for bodies of revolution at transonic speeds (National Aeronautics and Space Administration ;, 1973), by Lana M. Couch, Cuyler W. Brooks, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Some effects of control profile and control trailing-edge angle on the oscillating hinge-moment and flutter characteristics of flap-type controls at transonic speeds (National Aeronautics and Space Administration, 1960), by William C. Moseley, Thomas G. Gainer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Transonic flutter study of a 50.5 ̊cropped-delta wing with two rearward-mounted nacelles (National Aeronautics and Space Administration ;, 1974), by M. C. Sandford, Irving Abel, Charles L. Ruhlin, and Langley Research Center (page images at HathiTrust)
Effect of canard location and size on canard-wing interference and aerodynamic-center shift related to maneuvering aircraft at transonic speeds (National Aeronautics and Space Administration ;, 1974), by Blair B. Gloss and Langley Research Center (page images at HathiTrust)
Performance, stability, and control characteristics at transonic speeds of three V/STOL airplane configurations with wings of variable sweep (National Aeronautics and Space Administration, 1960), by Arvo A. Luoma, William J. Alford, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Investigation of some effects of flexibility on the lift and pitching-moment characteristics of a series of low-aspect- ratio wing-body combinations at transonic speeds (National Aeronautics and Space Administration, 1960), by Robert V. Doggett, A. Gerald Rainey, and Langley Research Center (page images at HathiTrust)
Aerodynamic characteristics of a swept-wing cruise missile at Mach numbers from 0.50 to 2.86 (National Aeronautics and Space Administration ;, 1972), by M. Leroy Spearman, Ida K. Collins, and Langley Research Center (page images at HathiTrust)
Dynamics of high-drag probe shapes at transonic speeds (National Aeronautics and Space Administration, 1971), by Robert I. Sammonds, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Measurements of surface-pressure and wake-flow fluctations in the flow field of a Whitcomb supercritical airfoil (National Aeronautics and Space Administration ;, 1977), by Frederick W. Roos, Dennis W. Riddle, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-6582 (National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1971), by Frank R. Bailey, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Some effects of tip fins of wing flutter characteristics (National Aeronautics and Space Administration ;, 1974), by Robert C. Goetz, Robert V. Doggett, and Langley Research Center (page images at HathiTrust)
Investigation of new radar-data-reduction techniques used to determine drag characteristics of a free-flight vehicle (National Aeronautics and Space Administration ;, 1974), by Gerard E. Woodbury, John W. Wallace, and Langley Research Center (page images at HathiTrust)
A summary of information on support interference at transonic and supersonic speeds (NACA, 1954), by Eugene S. Love, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
On slender-body theory at transonic speeds (NACA, 1954), by Keith C. Harder, E. B. Klunker, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
A study of the flow over a 45À sweptback wing -fuselage combination at transonic Mach numbers (NACA, 1952), by Richard T. Whitcomb, Thomas C. Kelly, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Some examples of the applications of the transonic and supersonic area rules to the prediction of wave drag (NACA, 1957), by Robert L. Nelson, Clement J. Welsh, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
On the range of applicability of the transonic area rule (NACA, 1954), by John R. Spreiter, United States National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
An evaluation of two cooling-air ejectors in flight at transonic speeds (National Advisory Committee for Aeronautics, 1954), by L. Stewart Rolls, C. Dewey Havill, and Ames Research Center (page images at HathiTrust)
A transonic investigation of the effects of semisubmerged-store cavities and of slots on the zero-lift drag of a body of revolution (National Advisory Committee for Aeronautics, 1957), by George H. Holdaway, Elaine W. Hatfield, Minor R. Wallace, and Ames Research Center (page images at HathiTrust)
Influence of the body flow field on the zero-lift wave drag of wing-body combinations modified in accordance with the transonic area rule (National Advisory Committee for Aeronautics, 1956), by William A. Page and Ames Research Center (page images at HathiTrust)
Effect of high rotor pressure-surface diffusion on performance of a transonic turbine (National Advisory Committee for Aeronautics, 1955), by James W. Miser, Daniel E. Monroe, Warner L. Stewart, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Effect of a reduction in stator solidity on performance of a transonic turbine (National Advisory Committee for Aeronautics, 1956), by James W. Miser, R. Y. Wong, Warner L. Stewart, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation of two-stage air-cooled turbine suitable for flight at mach number of 2.5. [Part] I, , Velocity-diagram study (National Advisory Committee for Aeronautics, 1956), by James W. Miser, Warner L. Stewart, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Drag measurements at transonic speeds of two bodies of fineness ratio 9 with different locations of maximum body diameter (National Advisory Committee for Aeronautics, 1948), by Jim Rogers Thompson, Max C. Kurbjun, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Aerodynamic characteristics of a wing with quarter-chord line swept back 35°, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section. Transonic-bump method (National Advisory Committee for Aeronautics, 1949), by William C. Sleeman, William D. Morrison, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range (National Advisory Committee for Aeronautics, 1951), by WIlliam T. Lauten, Herbert C. Nelson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Error in airspeed measurement due to static-pressure field ahead of an open-nose air-inlet model at transonic speeds (National Advisory Committee for Aeronautics, 1952), by Thomas C. O'Bryan, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Results of two experiments on flutter of high-aspect-ratio swept wings in the transonic speed range (National Advisory Committee for Aeronautics, 1952), by William T. Lauten, Burke R. O'Kelly, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Miscellaneous directional-stability data for several airplane-like configurations from rocket-model tests at transonic speeds (National Advisory Committee for Aeronautics, 1952), by Paul E. Purser, Jesse L. Mitchell, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
A preliminary investigation of aerodynamic characteristics of small inclined air outlets at transonic Mach numbers (National Advisory Committee for Aeronautics, 1953), by Paul E. Dewey, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
An experimental study of five annular air inlet configurations at subsonic and transonic speeds (National Advisory Committee for Aeronautics, 1953), by Carroll R. Bryan, Frank F. Fleming, Jospeh R. Milillo, Robert E. Pendley, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Measurements of fluctuating pressures on the wing of a sweptback wind-body combination in the Langley 16-foot transonic tunnel (National Advisory Committee for Aeronautics, 1953), by Louis W. Habel, Donald R. Bowman, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Application of transonic area rule to a sharp-lipped ducted nacelle (National Advisory Committee for Aeronautics, 1954), by Richard E. Walters, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
A flight investigation of the transonic area rule for a 52.5° sweptback wind-body configuration at Mach numbers between 0.8 and 1.6 (National Advisory Committee for Aeronautics, 1954), by Sherwood Hoffman, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
An investigation of the effects of a geometric twist on the aerodynamic loading characteristics of a 45° sweptback wing-body configuration at transonic speeds (National Advisory Committee for Aeronautics, 1954), by Claude V. Williams, United States. National Adviosry Committee for Aeronautics, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust; US access only)
An experimental study of a method of designing the sweptback-wing - fuselage juncture for reducing the drag at transonic speeds (National Advisory Committee for Aeronautics, 1955), by Robert R. Howell, Albert L. Braslow, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
The development of an 8-inch by 8-inch slotted tunnel for Mach numbers up to 1.28 (National Advisory Committee for Aeronautics, 1955), by B. H. Little, James M. Cubbage, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Flutter characteristics of swept wings at transonic speeds (National Advisory Committee for Aeronautics, 1955), by Laurence K. Loftin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Investigation at transonic speeds of aerodynamic characteristics of an unswept semielliptical air inlet in the root of a 45° sweptback wing (National Advisory Committee for Aeronautics, 1955), by Gene J. Bingham, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Investigation of transonic flutter characteristics of a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6 (National Advisory Committee for Aeronautics, 1957), by George W. Jones, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
An experimental investigation of the effects of Mach number, stabilizer dihedral, and fin torsional stiffness on the transonic flutter characteristics of a tee-tail (National Advisory Committee for Aeronautics, 1957), by Norman S. Land, Annie G. Fox, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Span loadings due to wing twist at transonic and supersonic speeds (National Advisory Committee for Aeronautics, 1957), by Frederick C. Grant, John P. Mugler, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Transonic flutter investigation of two 50° semispan modified-delta wings with tip ailerons (National Advisory Committee for Aeronautics, 1958), by Robert J. Platt, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Investigation of fixed-geometry supersonic inlets with bypass ducts for matching turbojet-engine air-flow requirements over a range of transonic and supersonic speeds (National Advisory Committee for Aeronautics, 1958), by Abraham Leiss, Walter J. Kouyoumjian, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation at transonic speeds of a fixed divergent ejector installed in a single-engine fighter model (National Advisory Committee for Aeronautics, 1958), by John M. Swihart, Charles E. Mercer, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Transonic longitudinal aerodynamic effects of sweeping up the rear of the fuselage of a rocket-propelled airplane model having no horizontal tail (National Advisory Committee for Aeronautics, 1955), by James H. Parks, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
An analysis of the pressure distribution measured on a body of revolution at transonic speeds in the slotted test section of the Langley 8-foot transonic tunnel (National Advisory Committee for Aeronautics, 1952), by Bruce B. Estabrooks, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Transonic longitudinal aerodynamic characteristics of a fighter-type airplane model with a low-aspect-ratio unswept wing and tee-tail (National Advisory Committee for Aeronautics, 1956), by Gerald Hieser, Charles F. Reid, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Transonic flow past a wedge profile with detached bow wave : general analytical method and final calculated results (National Advisory Committee for Aeronautics, 1951), by Walter G. Vincenti, Cleo B. Wagoner, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Two-dimensional transonic flow past airfoils (National Advisory Committee for Aeronautics, 1951), by Yung-Huai Kuo and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
On a solution of the nonlinear differential equation for transonic flow past a wave-shaped wall (National Advisory Committee for Aeronautics, 1951), by Carl Kaplan and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
An experimental investigation of transonic flow past two-dimensional wedge and circular-arc sections using a Mach-Zehnder interferometer (National Advisory Committee for Aeronautics, 1951), by Arthur E. Bryson and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
On transonic flow past a wave-shaped wall (National Advisory Committee for Aeronautics, 1952), by Carl Kaplan and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Laser anemometer measurements in a transonic axial-flow fan rotor (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Anthony J. Strazisar and Lewis Research Center (page images at HathiTrust)
Interference effects at transonic speeds of jets exhausting from the hull step of a model of a large, water-based airplane (National Aeronautics and Space Administration, 1960), by Beverly Z. Henry and United States National Aeronautics and Space Administration (page images at HathiTrust)
Transonic aerodynamic characteristics of a model of a proposed six-engine hull-type seaplane designed for supersonic flight (National Aeronautics and Space Administration, 1960), by Dewey E. Wornom and United States National Aeronautics and Space Administration (page images at HathiTrust)
Aerodynamic characteristics of a 0.0667-scale model of the North American X-15 research airplane at transonic speeds (National Aeronautics and Space Administration, 1959), by Robert S. Osborne and United States National Aeronautics and Space Administration (page images at HathiTrust)
Transonic flutter characteristics of a 45° sweptback wing with various distributions of ballast along the leading edge (National Aeronautics and Space Administration, 1959), by John R. Unangst and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Effect of wing thickness and sweep on the oscillating hinge-moment and flutter characteristics of a flap-type control at transonic speeds (National Aeronautics and Space Administration, 1959), by William C. Moseley, Thomas G. Gainer, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Longitudinal aerodynamic characteristics of a wing-body-tail model having a highly tapered, cambered 45° swept wing of aspect ratio 4 at transonic speeds (National Aeronautics and Space Administration, 1959), by F. E. West and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Transonic static aerodynamic characteristics of a blunt cone-cylinder body with flared afterbodies of various angles and base areas (National Aeronautics and Space Administration, 1959), by Roy M. Wakefield, Stuart L. Treon, Earl D. Knechtel, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Basic pressure measurements on a 0.0667-scale model of the North American X-15 research airplane at transonic speeds (National Aeronautics and Space Administration, 1960), by Robert S. Osborne, Virginia C. Stafford, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
An experimental study of the flutter of sails having a delta planform tested from a Mach number of 0.1 to a Mach number of 1.9 (National Aeronautics and Space Administration, 1961), by R. W. Hess, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A transonic wind-tunnel investigation of the static longitudinal and lateral aerodynamic characteristics of a proposed hypersonic glider with several booster configurations (National Aeronautics and Space Administration, 1960), by Ralph P. Bielat, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Dynamic longitudinal and directional stability derivatives for a 45° sweptback-wing airplane model at transonic speeds (National Aeronautics and Space Administration, 1959), by Ralph P. Bielat, Harleth G. Wiley, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
An investigation of the pitching-moment contribution of a high horizontal tail on an unswept-wing and body combination at mach numbers from 0.80 to 1.40 (National Aeronautics and Space Administration, 1959), by Garth W. Lippmann and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Experimental investigation of a transonic compressor cascade and test results for four blade sections (National Aeronautics and Space Administration, 1960), by James C. Emery, Willard R. Westphal, James C. Dunavant, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Stability and control characteristics of a 0.0667-scale model of the final version of the North American X-15 research airplane (configuration 3) at transonic speeds (National Aeronautics and Space Administration, 1963), by Robert S. Osborne, George M. Ware, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Observations on the flows past blunt bodies at transonic speeds (National Aeronautics and Space Administration, 1960), by Philip E. Everhart, Walter F. Lindsey, and United States National Aeronautics and Space Administration (page images at HathiTrust)
An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47° sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Langley 8-foot high-speed tunnel (National Advisory Committee for Aeronautics, 1951), by Ralph P. Bielat, Domenic A. Coppolino, Daniel E. Harrison, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of longitudinal wings position on the pressure characteristics at transonic speeds of a 45° sweptback wing-fuselage model (National Advisory Committee for Aeronautics, 1953), by William Solomon, James W. Schmeer, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effects of fences, leading-edge chord-extensions, bound-layer ramps, and trailing-edge flaps on the longitudinal stability of a twisted and cambered 60° sweptback-wing--indented-body configuration at transonic speeds (National Advisory Committee for Aeronautics, 1954), by Thomas L. Fischetti, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
The effects of wing incidence on the aerodynamic loading characteristics of a sweptback wing-body combination at transonic speeds (National Advisory Committee for Aeronautics, 1954), by Harold L. Robinson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
An experimental transonic investigation of a 45° sweptback wing-body combination with several types of body indentation with theoretical comparisons included (National Advisory Committee for Aeronautics, 1954), by Melvin M. Carmel, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Characteristics of loads in rough air at transonic speeds of rocket-powered models of a canard and a conventional-tail configuration (National Advisory Committee for Aeronautics, 1955), by A. James Vitale and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Transonic investigation at lifting conditions of streamline contouring in the sweptback-wing-fuselage juncture in combination with the transonic area rule (National Advisory Committee for Aeronautics, 1956), by William E. Palmer, Albert L. Braslow, Robert R. Howell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Effects of two leading-edge modifications on the aerodynamic characteristics of a thin low-aspect-ratio delta wing at transonic speeds (National Advisory Committee for Aeronautics, 1956), by John P. Mugler and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Steady loads due to jet interference on wings, tails, and fuselages at transonic speeds (National Advisory Committee for Aeronautics, 1957), by John M. Swihart, Norman L. Crabill, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of wing-mounted external stores on the lift and drag of the Douglas D-558-II research airplane at transonic speeds (National Advisory Committee for Aeronautics, 1957), by Jack Nugent, Flight Research Center (U.S.), and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Computation of the transonic flow over a wedge with detached shock wave by the method of steepest descent (Aberdeen, Maryland : Aberdeen Proving Ground, 1953., 1953), by Joseph W. Fischbach, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
Effects of overhang balance on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60 degree delta wing at transonic and supersonic speeds (Washington, D.C. : National Advisory Committee for Aeronautics, 1954., 1954), by Lawrence D. Guy, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a diamond-plan-form wing aspect ration 3.08 and a low, swept horizontal tail (Washington, D.C. : National Advisory Committee for Aeronautics, 1954., 1954), by Alan B. Kehlet, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Transonic wind-tunnel investigation of the effects of sweepback and thickness ratio on the wing loads of a wing-body combination of aspect ratio 4 and taper ratio 0.6 (Washington, D.C. : National Advisory Committee for Aeronautics, [1955], 1955), by Robert J. Platt, Joseph D. Brooks, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Loads on thin wings at transonic speeds (Washington, D.C. : National Advisory Committee for Aeronautics, 1955., 1955), by Don D. Davis, Gerald Hieser, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Loads on external stores at transonic and supersonic speeds (Washington, D.C. : National Advisory Committee for Aeronautics, 1955., 1955), by Lawrence D. Guy, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Investigation at transonic speeds of the hinge-moment characteristics of a 1/8-scale model of the X-1E aileron (Washington, D.C. : National Advisory Committee for Aeronautics, 1955., 1955), by William C. Moseley, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Transonic investigation of aerodynamic characteristics of a swept-wing fighter-airplane model with leading-edge droop in combination with outboard chord-extensions and notches (Washington, D.C. : National Advisory Committee for Aeronautics, [1956], 1956), by Charles F. Whitcomb, Harry T. Norton, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections (Washington, D.C. : National Advisory Committee for Aeronautics, [1956], 1956), by Jack F. Runckel, Edwin E.. Lee, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
A theory for base pressures in transonic and supersonic flow (Mechanical Engineering Dept., Univ. of Illinois, 1955), by Helmut Hans Korst, M. E. Childs, R. H. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust)
A theory for base pressures in transonic and supersonic flow (Mechanical Engineering Dept., Univ. of Illinois, 1962), by Helmut Hans Korst, M. E. Childs, R. H. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust)
Compressible two-dimensional jet mixing at constant pressure : tables of auxiliary functions for fully developed mixing profiles (Mechanical Engineering Dept., University of Illinois, 1955), by Helmut Hans Korst, M. E. Childs, R. H. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust)
Truncated cone in supersonic flight at zero angle of attack : surface pressure coefficients, drag coefficients, and shock front configurations (Mechanical Engineering Dept., Engineering Experiment Station, University of Illinois, 1960), by W. L. Chow, C.C. Tsung, Helmut Hans Korst, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust)
Transonic flow past a wedge at zero angle of attack (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1952., 1952), by Leon Trilling, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Massachusetts Institute of Technology. Aeronautical Engineering Department (page images at HathiTrust)
On the flow over a finite wedge in the lower transonic region (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1956., 1956), by Hideo Yoshihara, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust)
Demonstration of a transonic box method for unsteady aerodynamics of planar wings (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1966., 1966), by J. J. Olsen and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
An approximate solution of unsteady transonic flow problems (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by Kenneth R. Kimble, Jain-Ming Wu, Air Force Flight Dynamics Laboratory (U.S.), and University of Tennessee (System). Space Institute (page images at HathiTrust)
Buffet characteristics of the model F-4 airplane in the transonic flight regime (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1970., 1970), by Marshall Cohen, Air Force Flight Dynamics Laboratory (U.S.), McDonnell Aircraft Company, and United States. Air Force. Systems Command (page images at HathiTrust)
Mass injection and jet flow simulation effects on transonic afterbody drag (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1978., 1978), by Wladimiro Calarese, Ronald E. Walterick, United States. Air Force. Systems Command, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Development of an empirically based computer program to predict the aerodynamic characteristics of aircraft. Volume I, Empirical methods. (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1973., 1973), by Roy T. Schemensky, Air Force Flight Dynamics Laboratory (U.S.), and General Dynamics Corporation. Convair Division (page images at HathiTrust)
A bibliography of recent developments in unsteady transonic flow (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979-1980., 1979), by Christopher J. Borland, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Company (page images at HathiTrust)
Transonic wind tunnel tests on an oscillating wing with external stores. Part II, The clean wing (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979., 1979), by H. Tijdeman, C. M. Siebert, P. Schippers, R. Roos, R. Poestkoke, A. J. Persoon, A. N. Kraan, J. W. G. van Nunen, Nationaal Lucht- en Ruimtevaartlaboratorium (Netherlands), and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
High speed smoke flow visualization (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by Stephen M. Batill, T. J. Mueller, Robert C. Nelson, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and University of Notre Dame. Department of Aerospace and Mechanical Engineering (page images at HathiTrust)
Finite element analysis of transonic flow (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by S. T. K. Chan, M. R. Brashears, Air Force Flight Dynamics Laboratory (U.S.), and Huntsville Research & Engineering Center (page images at HathiTrust)
Small disturbance transonic flows about oscillating airfoils (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by R. M. Traci, H. K. Cheng, J. L Farr, E. D. Albano, Air Force Flight Dynamics Laboratory (U.S.), and inc Science Applications (page images at HathiTrust)
Unsteady aerodynamic pressures in transonic flow (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by L. V. Andrew, Air Force Flight Dynamics Laboratory (U.S.), and North American Rockwell Corporation (page images at HathiTrust)
An integral equation method for boundary interference in a perforated-wall wind tunnel at transonic speeds (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by E. M. Kraft, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
An investigation of the half-model reflection-plane technique for dynamic stability testing at transonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by T. O. Shadow, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Application of a three-dimensional steady and unsteady full potential method for transonic flow computations (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1984, 1984), by J. B. Malone, N. L. Sankar, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-Georgia Company (page images at HathiTrust)
Investigations of the interaction of boundary layer and shock waves in transonic flow (Wright-Patterson Air Force Base, Ohio : United States, Air Force, Air Materiel Command, 1948, 1948), by H. W. Liepmann, Jospeh Platt, Jean G. Goppert, California Institute of Technology, and United States. Air Force. Air Matériel Command (page images at HathiTrust)
Interference on a model afterbody from downstream support hardware at transonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by Earl A. Price, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Comparative experimental and theoretical studies of the flutter of flat panels in a low supersonic flow (Washington, D.C. : United States Air Force, Office of Scientific Research, 1961., 1961), by M. H. Lock, Y. C. Fung, United States. Air Force. Office of Scientific Research, and California Institute of Technology (page images at HathiTrust)
Exhaust plume temperature effects on nozzle afterbody performance over the transonic Mach number range (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1974., 1974), by C. E. Robinson, M. Dean High, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
An investigation of sting interference effects on an oscillating cone in transonic flow (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by Frederick B. Cyran, J. P. Christopher, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Solution-adaptive calculation of unsteady blade row interactions in transonic turbomachinery (Wright-Patterson Air Force Base, Ohio : Aero Propulsion and Power Directorate, Wright Laboratory, Air Force Materiel Command, United States Air Force, 1996., 1996), by Scott M. Richardson and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
Asymptotic far field conditions for unsteady subsonic and transonic flows (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1983., 1983), by Karl Gottfried Guderley, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and University of Dayton. Research Institute (page images at HathiTrust)
Wind tunnel tests of a 0.06-scale B-1 model at Mach numbers from 0.60 to 1.60 : phase IV (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by C. J. Spurlin, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Calibration of the AEDC-PWT 16-ft transonic tunnel with the propulsion test section at various Reynolds numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by F. M. Jackson, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Jet simulation techniques : simulation of temperature effects by altering gas composition (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1979., 1979), by W. L. Peters, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
A study of the characteristics of transonic buffet pressures on a large hammerhead configuration (Los Angeles, California : Space Systems Division, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1967., 1967), by H. E. Wang, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust)
An investigation of F-16 nozzle-afterbody forces at transonic Mach numbers with emphasis on support system interference (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1979., 1979), by Earl A. Price, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Numerical calculation of the subsonic and transonic turbulent boundary layer on an infinite yawed airfoil (Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by John C. Adams, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Unsteady viscous-inviscid interaction procedures for transonic airfoil flows (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1984., 1984), by Tracy Donegan, United States. Air Force. Arnold Air Force Base, Arnold Engineering Development Center, and Calspan Field Services (page images at HathiTrust)
An experimental and analytic investigation of a transonic shock-wave/boundary-layer interaction (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by M. C. Alstatatt, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Combined asymptotics and numerical methods in transonic store interactions (Arlington, Virginia. : Air Force Office of Scientific Research, 2002., 2002), by N. Malmuth, A. V. Fedorov, Vladimir Shalaev, Moskovskiĭ fiziko-tekhnicheskiĭ institut, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Inlet performance characteristics of a generalized 1/5.2-scale aircraft model at transonic and supersonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by Jimmy Walker, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
An investigaion of boattail geometry and Reynolds number effects on forebody and afterbody drag at transonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by A. V. Spratley, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Flow-field study about a hemisphere-cylinder in the transonic and low supersonic Mach number range (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1975., 1975), by T. Hsieh, B. M. Majors, W. T. Strike, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
An investigation of separated flow about a hemisphere-cylinder at 0- to 19-deg incidence in the Mach number range from 0.6 to 1.5 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by T. Hsieh, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Transonic wing/store flow-field measurement using a laser velocimeter (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by F. L. Heltsley, D. Brayton, F. L. Crosswy, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Skin-friction measurements at subsonic and transonic Mach numbers with embedded-wire gages (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by D. W. Sinclair, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
3-D composite velocity solutions for subsonic/transonic flow over forebodies and afterbodies (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Wright Research Development Center, Air Force Systems Command, United States Air Force, 1989., 1989), by Raymond E. Gordnier, Inc Universal Energy Systems, Wright Research and Development Center, Air Force Flight Dynamics Laboratory (U.S.), and United States. Air Force. Systems Command (page images at HathiTrust)
A generic nonlinear aeroelastic method with semi-empirical nonlinear unsteady aerodynamics. Volume 2, Nonlinear users instructions (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 1999., 1999), by Atlee M. Cunningham, Lockheed Martin. Tactical Aircraft Systems, and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
A generic nonlinear aeroelastic method with semi-empirical nonlinear unsteady aerodynamics. Volume 1, Techynical discussion (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 1999., 1999), by Atlee M. Cunningham, Lockheed Martin. Tactical Aircraft Systems, and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
An examination of several high resolution schemes applied to complex problems in high speed flows (Wright-Patterson Air Force Base, Ohio : Fliight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, 1992., 1992), by Norbert Kroll, Datta V. Gaitonde, Michael J. Aftosmis, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and Technische Universität Braunschweig (page images at HathiTrust)
Two-dimensional Navier-Stokes solution of the flow over a thick supercritical airfoil with strong shock-induced separation (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1988., 1988), by Don W. Kinsey, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Inlet performance characteristics of a generalized 1/4-scale tactical aircraft models at transonic and supersonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1971., 1971), by R. F. Lauer, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
On the theory of transonic aileron buzz (Cambridge, Massachusetts : Massachusetts Institute of Technology, Fluid Dynamics Research Laboratory, 1960., 1960), by Wiktor Eckhaus, Massachusetts Institute of Technology. Fluid Dynamics Research Laboratory, and United States. Air Force. Office of Scientific Research (page images at HathiTrust; US access only)
A mehod for the prediction of the effects of free-stream disturbances on boundary-layer transition (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by J. A. Benek, M. Dean High, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Research on adaptive wall wind tunnels (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1978., 1978), by Robert J. Vidal, J. C Erickson, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Calspan Corporation (page images at HathiTrust)
Evaluation of Reynolds number and tunnel wall porosity effects on nozzle afterbody drag at transonic mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by C. E. Robinson, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
Influences of sway braces and mounting gaps on the static aerodynamic loading of external stores (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by R. E. Dix, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Aerodynamic and cold jet plume geometry characteristics of the Army free rocket at transonic mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1975., 1975), by E. S. Washington, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
Evaluation of boattail geometry and exhaust plume temperature effects on nozzle afterbody drag at transonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by L. L. Galigher, R. C. Bauer, Steven F. Yaros, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
Theoretical and experimental investigation of supersonic combustion (Polytechnic Institute of Brooklyn, Dept. of Aerospace Engineering and Applied Mechanics, 1962), by Antonio Ferri, Victor Zakkay, Paul A. Libby, and Polytechnic Institute of Brooklyn. Dept. of Aerospace Engineering and Applied Mechanics (page images at HathiTrust)
Pressure distributions on three bodies of revolution to determine the effect of Reynolds number up to and including the transonic speed range (NACA, 1953), by John M. Swihart, Charles F. Whitcomb, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of passive venting on static pressure distributions in cavities at subsonic and transonic speeds (National Aeronautics and Space Administration, Langley Research Center, 1994), by Robert L. Stallings and United States National Aeronautics and Space Administration (page images at HathiTrust)
Transonic pressure measurements and comparison of theory to experiment for an arrow-wing configuaration / summary report (National Aeronautics and Space Administration ;, 1977), by Marjorie E. Manro, Boeing Commercial Airplane Company, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Grid network generation with adaptive boundary points for projectiles at transonic speed (Aberdeen Proving Ground, Maryland : U.S. Army Armament Research and Development Command, Ballistic Research Laboratory, 1983., 1983), by Hsu Chen-Chi, U.S. Army Ballistic Research Laboratory, and United States. Army Armament Research and Development Command (page images at HathiTrust)
Similarity parameters and their sensitivity for transonic airframe exhaust nozzle interactions (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1973., 1973), by Gerald Roffe, Gabriel Miller, Air Force Flight Dynamics Laboratory (U.S.), Advanced Technology Laboratories, and United States. Air Force. Systems Command (page images at HathiTrust)
Recent applications of CFD to the aerodynamics of army projectiles (Aberdeen Proving Ground, Maryland : United States Army Research Laboratory, 1992., 1992), by Walter B. Sturek, Paul Weinacht, Jubaraj Sahu, Charles J. Nietubicz, and U.S. Army Research Laboratory (page images at HathiTrust)
The transonic free flight range (Aberdeen Proving Ground, Maryland : Ballistic Research Laboratories, 1958., 1958), by Walker K. Rogers and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
Static and Magnus aerodynamic characteristics of the 155mm, M483 projectile and its modifications (Dover, New Jersey : Picatinny Arsenal, 1976., 1976), by R. W. Kline, T. D. Hoffman, and Picatinny Arsenal (1907-1977) (page images at HathiTrust)
Navier-Stokes computations of projectile base flow at transonic speeds with and without base injection (Aberdeen Proving Ground, Maryland : U.S. Army Armament Research and Development Command, Ballistic Research Laboratory, 1983., 1983), by Jubaraj Sahu, J. L. Steger, Charles J. Nietubicz, U.S. Army Ballistic Research Laboratory, and United States. Army Armament Research and Development Command (page images at HathiTrust)
Boundary-layer trip effectiveness and computations of aerodynamic heating for XM797 nose-tip configurations (Aberdeen Proving Ground, Maryland : Ballistic Research Laboratory, 1983., 1983), by Walter B. Sturek, Donald C. Mylin, Lyle D. Kayser, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
An investigation of the effectiveness of several devices in simulating a rocket plume at free stream Mach numbers 0.9 to 1.2 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, 1971., 1971), by James Robert Burt, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
Normal force effectiveness of several fin planforms with streamwise gaps at Mach numbers of 0.8 to 5.0 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research and Development Directorate, Advanced Systems Laboratory, 1970., 1970), by C. W. Dahlke, W. Pettis, Redstone Arsenal (Ala.), and United States. Army. Missile Command. Research and Development Directorate (page images at HathiTrust)
Inviscid flow analysis on body of revolution with slender cruciform canted delta fins at small angle of incidence (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1975., 1975), by N. Uchiyama, J. M. Wu, Redstone Arsenal (Ala.), University of Tennessee (System). Space Institute, and Development United States. Army. Missile Command. Research (page images at HathiTrust)
An experimental investigation of the aerodynamic characteristics of several nose-mounted canard configurations at transonic Mach numbers (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1974., 1974), by James R Burt, Redstone Arsenal (Ala.), Chrysler Corporation, and Development United States. Army. Missile Command. Research (page images at HathiTrust)
Transonic shock-turbulent boundary layer interactions on spinning axisymmetric bodies at zero angle of attack. (Aberdeen Proving Ground, Maryland : U.S. Army Armament Research and Development Command, Ballistic Research Laboratory, 1983., 1983), by George R. Inger, U.S. Army Ballistic Research Laboratory, and United States. Army Armament Research and Development Command (page images at HathiTrust)
Navier-Stokes computational study of axisymmetric transonic turbulent flows with a two-equation model of turbulence (Aberdeen Proving Ground, Maryland : U.S. Army Ballistic Research Laboratory, 1985., 1985), by Jubaraj Sahu and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
Transonic wind tunnel investigation of thrust effects on the longitudinal stability characteristics of several body-fin configurations : sting-mounted model with normal-jet plume simulator (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1974., 1974), by James H. Henderson, Redstone Arsenal (Ala.), Chrysler Corporation, and Development United States. Army. Missile Command. Research (page images at HathiTrust)
Approximate determination of jet contours near the exit of axially symmetrical nozzles as a basis for plume modeling (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Directorate for Research, Development, Enginering and Missile Systems Laboratory, 1972., 1972), by H. H. Korst, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
Computation of transonic flow past projectiles at angle of attack (Aberdeen Proving Ground, Maryland : U.S. Army Armament Research and Development Command, Ballistic Research Laboratory, 1979., 1979), by R. P. Reklis, F. R. Bailey, W. B. Sturek, U.S. Army Ballistic Research Laboratory, and United States. Army Armament Research and Development Command (page images at HathiTrust)
Guide to the operation of the MIRADCOM/UTSI computer program for plume induced sepertion at transonic speeds (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, Aeroballistics Directorate, Technology Laboratory, 1977., 1977), by D. J. Spring, Trevor H. Moulden, Redstone Arsenal (Ala.), United States. Army. Missile Command, and University of Tennessee (System). Space Institute (page images at HathiTrust)
Flight simulation of orbital and reentry vehicles. Part 3. Aerodynamics information required for six degrees of freedom simulation (Wright-Patterson Air Force Base, Ohio : Aerospace Medical Research Laboratories, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1961., 1961), by H. Buning, United States. Air Force. Systems Command. Aeronautical Systems Division, Aerospace Medical Research Laboratories (U.S.), and University of Michigan (page images at HathiTrust)
An investigation of streamwise body-fin gaps as a means of alleviating the adverse plume effects on missile longitudinal stability. (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1977., 1977), by James H. Henderson, Redstone Arsenal (Ala.), and Development United States. Army. Missile Command. Research (page images at HathiTrust)
An experimental investigation using a normal jet plume simulator to determine jet plume effects on a long slender rocket configuration at Mach numbers from 0.2 to 1.5 (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, 1977., 1977), by James H Henderson, G. Batiuk, Calvin Wayne Dahlke, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
Aerodynamic characteristics of a series of bodies with and without tails at Mach Numbers from 0.8 to 3.0 and angles of attack from 0 to 45 degrees (Redstone Arsenal, Alabama ; U.S. Army Missile Command, 1976., 1976), by Jimmie N. Derrick, Gary C. Winn, Donald J. Spring, Redstone Arsenal (Ala.), United States. Army. Missile Command, and University of Tennessee (System). Space Institute (page images at HathiTrust)
Subsonic and transonic similarity rules for jet-flapped wings (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1976., 1976), by Henry W. Woolard, Air Force Flight Dynamics Laboratory (U.S.), and United States. Air Force. Systems Command (page images at HathiTrust)
Investigation of jet plume effects on the longitudinal stability characteristics of a body of revolution with various fin configurations at Mach numbers from 0.2 to 2.3 : normal jet plume simulator (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1976., 1976), by James H. Henderson, Redstone Arsenal (Ala.), and Development United States. Army. Missile Command. Research (page images at HathiTrust)
Surface pressure measurements on a boattailed projectile shape at transonic speeds (Aberdeen Proving Ground, Maryland : Ballistic Research Laboratory, 1982., 1982), by Lyle D. Kayser, F. Whiton, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
Axisymmetric transonic flow calculations (Dover, New Jersey : Picatinny Arsenal, 1972., 1972), by Bruce S. Masson, Eugene Friedman, and Picatinny Arsenal (1907-1977) (page images at HathiTrust)
The aerodynamic coefficients of thin lifting airfoils at high subsonic speeds (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research Development and Command, United States Air Force, 1953., 1953), by Melvin Epstein, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Massachusetts Institute of Technology. Aeronautical Engineering Department (page images at HathiTrust)
The effect of wrap-around fins on aerodynamic stability and rolling moment variations (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1973., 1973), by C. W. Dahlke, J. C. Craft, Redstone Arsenal (Ala.), and Development United States. Army. Missile Command. Research (page images at HathiTrust)

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