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Aerodynamics -- Mathematical models

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• Aerodynamics
• Dynamics -- Mathematical models
• Fluid dynamics -- Mathematical models
• Gas dynamics -- Mathematical models
• Airplanes -- Mathematical models
• Mathematical models

• Aerodynamic heating -- Mathematical models
• Aerodynamic load -- Mathematical models
• Aerodynamics -- Computer simulation
• Aerodynamics, Hypersonic -- Mathematical models
• Aerodynamics, Supersonic -- Mathematical models
• Aerodynamics, Transonic -- Mathematical models
• Aeroelasticity -- Mathematical models
• Angle of attack (Aerodynamics) -- Mathematical models
• Body of revolution -- Mathematical models
• Boundary layer -- Mathematical models
• Cascades (Fluid dynamics) -- Mathematical models
• Downwash (Aerodynamics) -- Mathematical models
• Drag (Aerodynamics) -- Mathematical models
• Flutter (Aerodynamics) -- Mathematical models
• Gas flow -- Mathematical models
• Lift (Aerodynamics) -- Mathematical models
• Magnus effect -- Mathematical models
• Pitching (Aerodynamics) -- Mathematical models
• Rolling (Aerodynamics) -- Mathematical models
• Spin (Aerodynamics) -- Mathematical models
• Stability of airplanes -- Mathematical models
• Stability of rockets -- Mathematical models
• Stalling (Aerodynamics) -- Mathematical models
• Stratified flow -- Mathematical models
• Trajectory optimization -- Mathematical models
• Unsteady flow (Aerodynamics) -- Mathematical models
• Vortex-motion -- Mathematical models
• Wakes (Aerodynamics) -- Mathematical models
• Yawing (Aerodynamics) -- Mathematical models
• Aerofoils -- Aerodynamics -- Mathematical models
• Air ducts -- Aerodynamics -- Mathematical models
• Airplanes -- Wings -- Aerodynamics -- Mathematical models
• Balloons, Captive -- Aerodynamics -- Mathematical models
• Buildings -- Aerodynamics -- Mathematical models
• Compressors -- Aerodynamics -- Mathematical models
• Cone -- Aerodynamics -- Mathematical models
• Gas-turbines -- Aerodynamics -- Mathematical models
• Gliders (Aeronautics) -- Aerodynamics -- Mathematical models
• Guided missiles -- Aerodynamics -- Mathematical models
• Helicopters -- Aerodynamics -- Mathematical models
• Launch vehicles (Astronautics) -- Aerodynamics -- Mathematical models
• Lift fans -- Aerodynamics -- Mathematical models
• Noses (Aircraft) -- Aerodynamics -- Mathematical models
• Parachutes -- Aerodynamics -- Mathematical models
• Plates (Engineering) -- Aerodynamics -- Mathematical models
• Private planes -- Aerodynamics -- Mathematical models
• Projectiles, Aerial -- Aerodynamics -- Mathematical models
• Propellers, Aerial -- Aerodynamics -- Mathematical models
• Research aircraft -- Aerodynamics -- Mathematical models
• Rockets (Aeronautics) -- Fins -- Aerodynamics -- Mathematical models
• Rotors (Helicopters) -- Aerodynamics -- Mathematical models
• Space shuttles -- Aerodynamics -- Mathematical models
• Space vehicles -- Aerodynamics -- Mathematical models
• Tubes -- Aerodynamics -- Mathematical models
• Tunnels -- Aerodynamics -- Mathematical models
• Turbines -- Aerodynamics -- Mathematical models
• Turbomachines -- Aerodynamics -- Mathematical models
• Vehicles -- Aerodynamics -- Mathematical models
• Vertically rising aircraft -- Aerodynamics -- Mathematical models

• User's manual for interactive LINEAR : a FORTRAN program to derive linear aircraft models (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1988), by Robert F. Antoniewicz, Brian P. Patterson, Eugene L. Duke, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Panel methods : an introduction (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Larry L. Erickson and Ames Research Center (page images at HathiTrust)
• Application of supersonic linear theory and hypersonic impact methods to three nonslender hypersonic airplane concepts at mach numbers from 1.10 to 2.86 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Jimmy L. Pittman, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Sonic-boom wave-front shapes and curvatures associated with maneuvering flight (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Raymond L. Barger, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Application of a numerically generated orthogonal coordinate system to the solution of inviscid axisymmetric supersonic flow over blunt bodies (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by H. Harris Hamilton, Randolph A. Graves, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Development and validation of a combined rotor-fuselage induced flow-field computational method (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Carl E. Freeman, Army Research and Technology Laboratories (U.S.). Structures Laboratory, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Surrogate-equation technique for simulation of steady inviscid flow (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Gary M. Johnson, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• User's manual for MMLE3, a general FORTRAN program for maximum likelihood parameter estimation (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Richard E. Maine, Kenneth W. Iliff, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Steady subsonic flow around finite-thickness wings (National Aeronautics and Space Administration ;, 1975), by Ching-Chiang Kuo, L. Morino, Langley Research Center, and Boston University. Dept. of Aerospace Engineering (page images at HathiTrust)
• A computer program for wing subsonic aerodynamic performance estimates including attainable thrust and vortex lift effects (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Harry W. Carlson, Kenneth B. Walkley, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Computation of transonic potential flow about three-dimensional inlets, ducts, and bodies (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Theodore A. Reyhner, Boeing Commercial Airplane Company, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Some aspects of essentially nonoscillatory (ENO) formulations for the Euler equations (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Sukumar R. Chakravarthy, Langley Research Center, and Rockwell International. Science Center (page images at HathiTrust)
• A Review of near-wall Reynolds-stress closures (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Ronald M. C. So, Langley Research Center, and Arizona State University. College of Engineering and Applied Sciences (page images at HathiTrust)
• Optimum airplane flight paths (National Aeronautics and Space Administration, 1959), by Placido Cicala (page images at HathiTrust)
• Analytical investigation of the motion of a clamshell-type heat shield on deployment from a parent vehicle in the atmosphere (National Aeronautics and Space Administration ;, 1966), by Ross L. Goble and Langley Research Center (page images at HathiTrust)
• Reduction of incremental load factor acceleration data to gust statistics (FAA Technical Center ;, 1994), by J. B. de Jonge, Nationaal Lucht- en Ruimtevaartlaboratorium (Netherlands), Federal Aviation Administration Technical Center (U.S.), and Netherlands. Rijksluchtvaartdienst (page images at HathiTrust)
• Electrical characteristics of spark generators for automotive ignition (National Advisory Committee for Aeronautics, 1926), by R. B. Brode, F. B. Silsbee, D. W. Randolph, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Unsteady aerodynamics for advanced configurations. Part IV. Application of the supersonic mach box method to intersecting planar lifting surfaces (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by M. T. Moore, L. V. Andrew, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and North American Aviation. Space and Information Systems Division (page images at HathiTrust)
• Aerodynamic testing in a free-flight spark range (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1997., 1997), by G. L. Winchenbach, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Feedback control for aerodynamics : preprint (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 2006., 2006), by R. Chris Camphouse, James H. Myatt, Seddik M. Djouadi, and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Unsteady aerodynamics for advanced configurations. Part V. Unsteady potential flow around slender bodies at angles of attack (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by T. C. Li, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and North American Aviation. Space and Information Systems Division (page images at HathiTrust)
• Stability theory for cross hatching. Part I, Linear stability theory (Norton Air Force Base, California : Space and Missile Systems Organization, Air Force Systems Command, United States Air Force, 1972., 1972), by Lester Lees, Denny R. S. Ko, T. Kubota, United States. Air Force. Systems Command, Space and Missile Systems Organization (U.S.), and California Institute of Technology (page images at HathiTrust)
• Unsteady aerodynamics for advanced configurations. Part II A transonic box method for planar lifting surfaces (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by E. R. Rodemich, L. V. Andrew, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and North American Aviation. Space and Information Systems Division (page images at HathiTrust)
• Influence of structural and aerodynamic modeling on flutter analysis and structural optimization (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, 1991., 1991), by Alfred G. Struz, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and University of Oklahoma. School of Aerospace and Mechanical Engineering (page images at HathiTrust)
• The stability of compressible flows and transition through the speed of sound (Wright Field, Dayton, Ohio : Army Air Forces, Air Matériel Command, 1946., 1946), by John Pairman Brown and United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)
• Free-flight range tests of the MK76 MOD 5 Navy practice bobm at Mach numbers of 0.574 to 1.113 (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Guns, Rockets, and Explosives Division, Air Force Systems Command, United States Air Force, 1979., 1979), by G. L. Winchenback, Peter Daniels, Kenneth O. West, United States. Air Force. Systems Command, and Air Force Armament Laboratory (page images at HathiTrust)
• STORESIM : an integrated system for multi-body cfd simulations using unstructured, adaptive grids (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1996., 1996), by M. P. Reddy, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Computational mechanics approach for multidisciplinary nonlinear sensitivity analysis (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 2001., 2001), by R. V. Grandhi, Wright State University, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Unsteady aerodynamics for advanced configurations. Part III. Elliptic-conical wing in linearized unsteady transonic flow (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by E. Albano, L. V. Andrew, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), Wright-Patterson Air Force Base. Flight Dynamics Laboratory, and North American Aviation. Space and Information Systems Division (page images at HathiTrust)
• An experimental investigation of a transverse jet ejecting from a flat plate into a subsonic free stream (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Advanced Systems Laboratory, Research and Engineering Directorate, 1970., 1970), by Troy A. Street, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• State-of-the-art engineering aeroprediction methods with emphasis on new semiempirical techniques for predicting nonlinear aerodynamics on complete missile configurations (Dahlgren, Virginia : Weapons Systems Department, Naval Surface Warfare Center, Dahlgren Division, 1993., 1993), by Frank G. Moore and Naval Surface Warfare Center (U.S.). Dahlgren Division (page images at HathiTrust)
• A general method for determining the aerodynamic characteristics of fan-in-wing configurations. (Fort Eustis, Virginia, U.S. Army Aviation Materiel Laboratories, 1967., 1967), by R. E. Wallace, N. M. Standen, M. B. Scholey, G. R. Saaris, P. E. Rubbert, K. A. Sundstrom, R. F. Gilbert, G. R. Hink, U.S. Army Aviation Materiel Laboratories, and Boeing Company (page images at HathiTrust)
• A general method for determining the aerodynamic characteristics of fan-in-wing configurations (Fort Eustis, Virginia : U.S. Army Aviation Materiel Laboratories, 1967., 1967), by U.S. Army Aviation Materiel Laboratories and Boeing Company. Commercial Airplane Division (page images at HathiTrust)
• Aerodynamics of tactical weapons to mach number 3 and angle of attack 15. Part II. Computer program and usage (Dahlgren, Virginia : Naval Surface Weapons Center, Warfare Analysis Department, 1977., 1977), by Roy C. Swanson, Frank G. Moore, and Naval Surface Warfare Center (U.S.). Dahlgren Division (page images at HathiTrust)

• Numerical studies of convective cooling for a locally heated skin (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Stephen J. Scotti and Langley Research Center (page images at HathiTrust)
• Rapid methods for calculating radiation transport in the entry environment (National Aeronautics and Space Administration, 1975), by William E. Nicolet, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Analysis of turbulent flow and heat transfer on a flat plate at high mach numbers with variable fluid properties (U.S. G.P.O.], 1959), by R. G. Deissler (page images at HathiTrust)
• Heat-transfer tests of 20-millimeter projectiles at a Mach number of 5 with an analysis by unsteady scaling laws to predict component temperature rises after firing for various free-flight conditions (National Aeronautics and Space Administration, 1961), by Robert L. Trimpi, Robert A. Jones, James G. Gallagher, and Langley Research Center (page images at HathiTrust)
• Heat-transfer and temperature distribution of a conical porous membrane during planetary entry (National Aeronautics and Space Administration ;, 1967), by Latif M. Jiji and Ames Research Center (page images at HathiTrust)
• Methods of predicting laminar heat rates on hypersonic vehicles (National Aeronautics and Space Administration, 1959), by Richard J. Wisniewski and Lewis Research Center (page images at HathiTrust)
• Inviscid hypersonic flow over a blunt body with high rates of mass and heat transfer (National Aeronautics and Space Administration ;, 1968), by E. Dale Martin and Ames Research Center (page images at HathiTrust)
• Unsteady stagnation-point heat transfer (National Aeronautics and Space Administration, 1959), by E. M. Sparrow and Lewis Research Center (page images at HathiTrust)
• Z-function solutions for the motion and heating during atmosphere entry from equatorial orbits of a rotating planet (National Aeronautics and Space Administration, 1963), by Frederick W. Boltz and Ames Research Center (page images at HathiTrust)
• Laminar skin-friction and heat-transfer parameters for a flat plate at hypersonic speeds in terms of free-stream flow properties (National Aeronautics and Space Administration, 1959), by James F. Schmidt and Lewis Research Center (page images at HathiTrust)
• Analysis of turbulent heat transfer, mass transfer, and friction in smooth tubes at high Prandtl and Schmidt numbers (National Advisory Committee for Aeronautics, 1954), by Robert G. Deissler and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of numerical techniques for predicting aerodynamic heating to flight vehicles (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979., 1979), by Arthur B. Lewis, Neil J. Sliski, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• A study of aerodynamic effects of isothermal and temperature gradient atmospheres on reentry trajectories (Polytechnic Institute of Brooklyn, 1962), by Leo Rute and Polytechnic Institute of Brooklyn. Dept. of Aerospace Engineering and Applied Mechanics (page images at HathiTrust)
• Transient temperature distributions in a sphere due to aerodynamic heating (Polytechnic Institute of Brooklyn, 1959), by Frederick V. Pohle, J. L. Boccio, and Polytechnic Institute of Brooklyn (page images at HathiTrust)
• A note on the transient temperature distribution in an orthotropic sphere due to aerodynamic heating (Polytechnic Institute of Brooklyn, 1961), by B. Venkatraman, Frederick V. Pohle, Sharad A. Patel, and Polytechnic Institute of Brooklyn (page images at HathiTrust)

• An unsteady lifting surface method for single rotation propellers (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Marc H. Williams, Lewis Research Center, and Purdue University. School of Aeronautics and Astronautics (page images at HathiTrust)
• The vortex lattice method for the rotor-vortex interaction problem (National Aeronautics and Space Administration ;, 1974), by Raghuveera Padakannaya, Langley Research Center, and Pennsylvania State University (page images at HathiTrust)
• Finite state modeling of aeroelastic systems (National Aeronautics and Space Administration ;, 1977), by Ranjan Vepa, Stanford University, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A program for calculating load coefficient matrices utilizing the force summation method, L218 (LOADS). (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by L. R. Anderson, R. D. Miller, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Calculation of the longitudinal aerodynamic characteristics of wing-flap configurations with externally blown flaps (National Aeronautics and Space Administration ;, 1976), by M. R. Mendenhall, Langley Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• Nonplanar wing load-line and slender wing theory (National Aeronautics and Space Administration ;, 1977), by John DeYoung, Vought Corporation. Hampton Technical Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Bivariate extreme value distributions (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by M. Elshamy, George C. Marshall Space Flight Center. Space Sciences Laboratory, and University of Alabama in Huntsville. Dept. of Mathematical Sciences (page images at HathiTrust)
• A method for predicting shock shapes and pressure distributions for a wide variety of blunt bodies at zero angle of attack (National Aeronautics and Space Administration ;, 1968), by George E. Kaattari and Ames 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)
• A method for predicting shock shapes and pressure distributions on two-dimensional airfoils at large angles of attack (National Aeronautics and Space Administration ;, 1973), by George E. Kaattari and Ames Research Center (page images at HathiTrust)
• A simplified mathematical model for calculating aerodynamic loading and downwash for midwing wing-fuselage combinations with wings of arbitrary plan form (National Advisory Committee for Aeronautics, 1953), by Martin Zlotnick, Samuel W. Robinson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Prediction of the pressure oscillations in cavities exposed to aerodynamic flow (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by D. L. Smith, L. L. Shaw, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)

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