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Noses (Aircraft)

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• Airplanes -- Fuselage
• Airplanes -- Nacelles
• Shells (Engineering)

• Noses (Aircraft) -- Aerodynamics
• Noses (Aircraft) -- Design and construction
• Noses (Aircraft) -- Research
• Noses (Aircraft) -- Safety measures
• Noses (Aircraft) -- Testing

• Nose cones (Aircraft)

• Investigation of the asymmetric aerodynamic characteristics of cylindrical bodies of revolution with variations in nose geometry and rotational orientation at angles of attack to 58ånd Mach numbers to 2 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Robert L. Kruse, Ames Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aerothermal tests of a 12.5⁰ cone at Mach 6.7 for various Reynolds numbers, angles of attack, and nose shapes (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Robert J. Nowak, L. Roane Hunt, Cindy W. Albertson, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of a series of bodies with variations in nose camber (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Barrett L. Shrout, Peter F. Covell, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Experimental aerodynamic characteristics for a cylindrical body of revolution with various noses at angles of attack from 0 ̊to 58 ̊and Mach numbers from 0.6 to 2.0 (National Aeronautics and Space Administration ;, 1974), by Leland H. Jorgensen, Edgar R. Nelson, and Ames Research Center (page images at HathiTrust)
• Experimental aerodynamic characteristics for bodies of elliptic cross section at angles of attack from 0 ̊to 58 ̊and Mach numbers from 0.6 to 2.0 (National Aeronautics and Space Administration ;, 1975), by Leland H. Jorgensen, Edgar R. Nelson, and Ames Research Center (page images at HathiTrust)
• Experimental aerodynamic characteristics for a cylindrical body of revolution with side strakes and various noses at angles of attack from 0 ̊to 58 ̊and Mach numbers from 0.6 to 2.0 (National Aeronautics and Space Administration ;, 1975), by Leland H. Jorgensen, Edgar R. Nelson, and Ames Research Center (page images at HathiTrust)
• Sonic-boom minimization with nose-bluntness relaxation (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Christine M. Darden, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Langley Research Center (page images at HathiTrust)
• A theoretical investigation of forebody shapes designed for natural laminar boundary-layer flow (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Raymond L. Barger, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Prediction of subsonic vortex shedding from forebodies with chines (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by M. R. Mendenhall, Daniel J. Lesieutre, Langley Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• Effects of forebody geometry on subsonic boundary-layer stability (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by S. S. Dodbele, Langley Research Center, Vigyan Research Associates, and Québec) International Conference on Numerical Methods in Laminar and Turbulent Flow (5th : 1987 : Montréal (page images at HathiTrust)
• Asymmetric lateral-directional characteristics of pointed bodies of revolution at high angles of attack (National Aeronautics and Space Administration ;, 1972), by Paul L. Coe, William Letko, Joseph R. Chambers, and Langley Research Center (page images at HathiTrust)
• NASA TN D-2900 (National Aeronautics and Space Administration :, 1965), by James M. Cubbage and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effect of forebody strakes on the aerodynamic characteristics in pitch and sideslip of a hypersonic airplane configuration at Mach numbers of 1.41, 2.01, and 6.86 (National Aeronautics and Space Administration, 1959), by Cornelius Driver and Langley Research Center (page images at HathiTrust)
• Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99. [Part] 2, Isentropic-spike all-external compression inlet (National Advisory Committee for Aeronautics, 1951), by L. J. Obery, G. W. Englert, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Effect of centerbody boundary-layer removal near the throat of three conical nose inlets at mach 1.6 to 2.0 (National Advisory Committee for Aeronautics, 1955), by Emil J. Kremzier, George A. Wise, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• An investigation of several NACA 1-series nose inlets with and without protruding central bodies at high-subsonic Mach numbers and at a Mach number of 1.2 (National Advisory Committee for Aeronautics, 1950), by Robert E. Pendley, Harold L. Robinson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flight determination of the drag and pressure recovery of an NACA 1-40-250 nose inlet at Mach numbers from 0.9 to 1.8 (National Advisory Committee for Aeronautics, 1951), by R. I. Sears, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• The effect of nose radius and shape of the aerodynamic characteristics of a fuselage and a wing-fuselage combination at angles of attack (National Advisory Committee for Aeronautics, 1953), by John P. Gapcynski, A. Warner Robins, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• A method for designing low-drag nose-inlet-body combinations for operation at moderate supersonic speeds (National Advisory Committee for Aeronautics, 1954), by Robert R. Howell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Local heat transfer to blunt noses at high supersonic speeds (National Advisory Committee for Aeronautics, 1957), by William E. Stoney, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Heat transfer and pressure measurement on a 5-inch hemispherical concave nose at a Mach number of 2.0 (National Advisory Committee for Aeronautics, 1958), by J. Thomas Markley, United States. National Adviosry Committee for Aeronautics, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• The Influence of very heavy fuselage mass loadings and long nose lengths upon oscillations in the spin (National Advisory Committee for Aeronautics, 1948), by Ralph W. Stone, Walter J. Klinar, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29° (National Advisory Committee for Aeronautics, 1958), by Charles B. Rumsey, Dorothy B. Lee, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• A compilation of longitudinal aerodynamic characteristics including pressure information for sharp-and blunt-nose cones having flat and modified bases (Sandia Corporation, 1965), by A. D. Foster, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust)
• Preliminary design aerodynamic prediction methodology for missiles with nose bluntness (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1978., 1978), by Charles W. Ingram, David Shida, Carter J. Dinkeloo, Karlheinz O. W. Ball, Air Force Flight Dynamics Laboratory (U.S.), and Systems Research Laboratories (page images at HathiTrust)
• Determination of factors governing selection and application of materials for ablation cooling of hypervelocity vehicles (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by John H. Bonin, Donald E. Taylor, Channon F. Price, Wright Air Development Center, and United States. Air Force. Air Research and Development Command (page images at HathiTrust; US access only)
• Free flight hypersonic heat transfer and boundary layer transition studies: HTV flights A-40 and A-41 (Wright-Patterson Air Force Base, Ohio : Aeronautical Research Laboratories, Air Force Research Division, Air Research and Development Command, United States Air Force, 1960., 1960), by James E. Brunk, Warren N. White, Aerospace Research Laboratories (U.S.), and Curtiss-Wright Corporation (page images at HathiTrust)
• Force and pressure tests on cones with simulated ablated noses at Mach numbers 8 and 16 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by J. S. Hahn, H. R. Little, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
• Static pressure on sharp and blunt cones in conical and parallel low-density flow (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1974., 1974), by Max Kinslow, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Mathematical fluid dynamic modeling of plasma stall-spin departure control (Arlington, Virginia. : Air Force Office of Scientific Research, 2007., 2007), by N. Malmuth, Victor Soloviev, Alexander Valerievich Fedorov, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• A comparison of transition Reynolds numbers from 12-in. and 40-in. supersonic tunnels (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by C. J. Schueler, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Research on hypersonic stability problems (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1974., 1974), by O. Walchner, Aerospace Research Laboratories (U.S.), and United States. Air Force. Office of Aerospace Research (page images at HathiTrust)
• Effects of unit Reynolds number, nose bluntness, and roughness on boundary layer transition (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Research and Development Command, United States Air Force, 1960., 1960), by J. Leith Potter, Jack D. Whitfield, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)

• Induced pressures on cylindrical rods with various nose drags and nose shapes at mach numbers of 17 and 21 (National Aeronautics and Space Administration :, 1962), by Robert D. Witcofski, Arthur Henderson, and United States National Aeronautics and Space Administration (page images at HathiTrust)

• Simplified input for certain aerodynamic nose configurations to the Grumman QUICK-geometry system : a KWIKNOSE User's Manual (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by Frederick L. Shope, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)

• Induced pressures on cylindrical rods with various nose drags and nose shapes at mach numbers of 17 and 21 (National Aeronautics and Space Administration :, 1962), by Robert D. Witcofski, Arthur Henderson, and United States National Aeronautics and Space Administration (page images at HathiTrust)

• Compilation of data on crew emergency escape systems (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, XXXX, 1966), by John O. Bull, Howard L. McDowell, Edward L. Serocki, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Company (page images at HathiTrust)

• Side forces on a tangent ogive forebody with a fineness ratio of 3.5 at high angles of attack and Mach numbers from 0.1 to 0.7 (National Aeronautics and Space Administration ;, 1977), by Earl R. Keener and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Subsonic wind-tunnel investigation of errors indicated by total-pressure tubes in the flow field of a body simulating the nose of the X-15 research airplane. William J. Alford Jr. (National Aeronautics and Space Administration :, 1962), by William J. Alford and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Laminar boundary-layer separation induced by flares on cylinders with highly cooled boundary layers at a Mach number of 15 (National Aeronautics and Space Administration :, 1965), by Donald M. Kuehn and Ames Research Center (page images at HathiTrust)
• Performance of a translating-double-cone axisymmetric inlet with cowl bypass at mach number from 2.0 to 3.5 (National Advisory Committee for Aeronautics, 1957), by James F. Connors, GeorgeA. Wise, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Metallurgical analysis of ablated aluminum alloy hemispheres (Polytechnic Institute of Brooklyn, Department of Aerospace Engineering and Applied Mechanics, 1962), by G. J. Fischer, R. Maciag, and Polytechnic Institute of Brooklyn. Dept. of Aerospace Engineering and Applied Mechanics (page images at HathiTrust; US access only)

Items below (if any) are from related and broader terms.

• Application of double Fourier series to the calculation of stresses caused by pure bending in a circular monocoque cylinder with a cut-out (The Polish Institute of Arts and Sciences in America, 1946), by Zbigniew Krzywoblocki and Polish Institute of Arts and Sciences in America (page images at HathiTrust)
• Principal effects of axial load on moment-distribution analysis of rigid structures (National Advisory Committee for Aeronautics, 1935), by Benjamin Wylie James and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Structural weight analysis: fuselage and shell structures. Jan., 1950. R-172. (Rand Corp., 1950), by William Raymond Micks and Rand Corporation (page images at HathiTrust)
• Effects of fuselage forebody geometry on low-speed lateral-directional characteristics of twin-tail fighter model at high angles of attack (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Peter C. Carr, William P. Gilbert, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center, and Hugh L. Dryden Flight Research Center (page images at HathiTrust)
• Improved tangent-cone method for the Aerodynamic Preliminary Analysis System (APAS) version of the Hypersonic Arbitrary-Body Program (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Christopher I. Cruz, Gregory J. Sova, and Langley Research Center (page images at HathiTrust)
• Experimental effects of fuselage camber on longitudinal aerodynamic characteristics of a series of wing-fuselage configurations at a mach of 1.41 (U.S. National Aeronautics and Space Administration ;, 1976), by Samuel M. Dollyhigh, Mary S. Adams, Odell A. Morris, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Experimental aerodynamic characteristics for slender bodies with thin wings at angles of attack from 0 ̊to 58 ̊and Mach numbers from 0.6 to 2.0 (National Aeronautics and Space Administration ;, 1976), by Leland H. Jorgensen, Michael H. Howell, and Ames Research Center (page images at HathiTrust)
• Pressures measured in flight on the aft fuselage and external nozzle of a twin-jet fighter (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Jack Nugent and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• A fuselage/tank structure study for actively cooled hypersonic cruise vehicles--summary (U.S. National Aeronautics and Space Administration ;, 1976), by C. J. Pirrello, J. E. Stone, A. H. Baker, McDonnell Douglas Corporation, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Calculation of three-dimensional, inviscid supersonic, steady flows (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1982), by Gino Moretti, Langley Research Center, Polytechnic Institute of New York, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Comparative study of fuselage tanks for liquid-methane-fueled supersonic aircraft (National Aeronautics and Space Administration, 1968), by Rene E. Chambellan, William A. Bevevino, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Low-speed characteristics of a variable-sweep supersonic transport model with a blended engine fuselage and engine-mounted tails (National Aeronautics and Space Administration, 1964), by Vernard E. Lockwood, Wilson E. Thompson, and Langley Research Center (page images at HathiTrust)
• Flight-test investigation of the aerodynamic characteristics and flow interference effects about the aft fuselage of the F111A airplane (National Aeronautics and Space Administration ;, 1974), by Norman V. Taillon and Flight Research Center (U.S.) (page images at HathiTrust)
• Low-speed static wind-tunnel investigation of a half-span fuselage and variable-sweep pressure wing model (National Aeronautics and Space Administration, 1971), by John E. Lamar, L. Wayne McKinney, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Interference between exhaust system and afterbody of twin-engine fuselage configurations (National Aeronautics and Space Administration ;, 1974), by Jack F. Runckel and Langley Research Center (page images at HathiTrust)
• A parametric study of effect of forebody shape on flow angularity at Mach 8 (National Aeronautics and Space Administration ;, 1974), by Charles B. Johnson, Don C. Marcum, and Langley Research Center (page images at HathiTrust)
• On the contribution of turbulent boundary layers to the noise inside a fuselage (NACA, 1956), by G. M. Corcos, H. W. Liepmann, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel corrections at high subsonic speeds particularly for an enclosed circular tunnel (NACA, 1952), by B. Göthert and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45° sweptback wing of aspect ratio 4 (National Advisory Committee for Aeronautics, 1957), by Kenneth P. Spreemann, William J. Alford, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Downwash characteristics and vortex-sheet shape behind a 63 degree swept-back wing-fuselage combination at a Reynolds number of 6,100,000 (National Advisory Committee for Aeronautics, 1952), by William H. Tolhurst and Ames Research Center (page images at HathiTrust)
• Tests of a small-scale NACA submerged inlet at transonic Mach numbers (National Advisory Committee for Aeronautics, 1950), by L. Stewart Rolls, George A. Rathert, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• General theory of wave-drag reduction for combinations employing quasi-cylindrical bodies with an application to swept-wing and body combinations (National Advisory Committee for Aeronautics, 1955), by Jack N. Nielsen and Ames Research Center (page images at HathiTrust)
• A buffet investigation at high subsonic speeds of wing-fuselage-tail combinations having sweptback wings with NACA 64A thickness distributions, fences, a leading-edge extension, and body contouring (National Advisory Committee for Aeronautics, 1957), by Fred B. Sutton, J. Walter Lautenberger, 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)
• 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)
• Pressure measurements on a body of revolution in the Langley 16-foot transonic tunnel and a comparison with free-fall data (National Advisory Committee for Aeronautics, 1952), by Joseph M. Hallissy, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Large-scale flight measurements of zero-lift drag and low-lift drag of 10 wing-body configurations at Mach numbers from 0.8 to 1.6 (National Advisory Committee for Aeronautics, 1953), by John D. Morrow, Robert L. Nelson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Pressure distribution measurements of the interference effect of the wing on the fuselage at mach numbers of 1.40 and 1.59 (National Advisory Committee for Aeronautics, 1952), by John P. Gapcynski, United States. National Adviosry Committee for Aeronautics, Langley Aeronautical Laboratory, and James W. Clark (page images at HathiTrust)
• Transonic wind-tunnel investigation of the effects of aspect ratio, spanwise variations in section thickness ratio, and a body indentation on the aerodynamic characteristics of a 45° sweptback wing-body combination (National Advisory Committee for Aeronautics, 1953), by Melvin M. Carmel, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Transient temperature distribution in an aerodynamically heated multiweb wing (National Advisory Committee for Aeronautics, 1953), by George E. Griffith, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• The performance of conical supersonic scoop inlets on circular fuselages (National Advisory Committee for Aeronautics, 1953), by Lowell E. Hasel, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• The effect of nose radius and shape of the aerodynamic characteristics of a fuselage and a wing-fuselage combination at angles of attack (National Advisory Committee for Aeronautics, 1953), by John P. Gapcynski, A. Warner Robins, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• 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)
• Effects of wing-body geometry on the lateral-flow angularities at subsonic speeds (National Advisory Committee for Aeronautics, 1956), by Frank S. Malvestuto, William J. Alford, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45° sweptback highly tapered wing in combination with basic and indented bodies (National Advisory Committee for Aeronautics, 1957), by Thomas L. Fischetti, United States. National Adviosry Committee for Aeronautics, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effect at high subsonic speeds of fuselage forebody strakes on the static stability and vertical-tail-load characteristics of a complete model having a delta wing (National Advisory Committee for Aeronautics, 1958), by Edward C. Polhamus, Kenneth P. Spreemann, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (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)
• Transonic wind-tunnel investigation of an unswept wing in combination with a systematic series of four bodies (National Advisory Committee for Aeronautics, 1953), by Bruce B. Estabrooks, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds. Aspect-ratio series (National Advisory Committee for Aeronautics, 1953), by Paul G. Fournier, Andrew L. Byrnes, 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)
• The effects of fuselage size on the low-speed longitudinal aerodynamic characteristics of a thin 60° delta wing with and without a double slotted flap (National Advisory Committee for Aeronautics, 1953), by John M. Riebe, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Investigation at mach numbers of 0.20 to 3.50 of a blended diamond wing and body combination of sonic design but with low wave-drag increase with increasing mach number (National Aeronautics and Space Administration, 1959), by George H. Holdaway, Elaine W. Hatfield, Jack A. Mellenthin, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• 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)
• 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)
• Transonic wind-tunnel investigation of aerodynamic-loading characteristics of a 2-percent-thick trapezoidal wing in combination with basic and indented bodies (National Advisory Committee for Aeronautics, 1957), by Thomas C. Kelly and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel (National Advisory Committee for Aeronautics, 1950), by Lowell E. Hasel, Archibald R. Sinclair, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1942), by Isidore G. Recant, Arthur R. Wallace, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Scientific fairing of veneer fuselages. (Dayton, Ohio : Airplane Engineering Division, Experimental Department, 1918., 1918), by United States. Bureau of Aircraft Production (page images at HathiTrust)
• Subsonic investigation of effects of body indentation on zero-lift drag characteristics of a 45° sweptback wing-body combination with natural and fixed boundary-layer transition through a range of Reynolds number from 1 x 10⁶ to 8 x 10⁶ (Washington, D.C. : National Advisory Committee for Aeronautics, 1954., 1954), by Gene J. Bingham, Albert L. Braslow, 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)
• The Conversion of aircraft ice crystal measurements into terms of liquid water using simulated data (Hanscom AFB, Massachusetts : Air Force Geophysics Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by R. O. Berthel and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Characterization of early stages of corrosion fatigue aircraft skin (U.S. Federal Aviation Administration, Office of Aviation Research ;, 1996), by C. G. Schmidt, SRI International, and United States. Federal Aviation Administration. Office of Aviation Research (page images at HathiTrust)
• Investigation of fuselage structure subject to widespread fatigue damage (Federal Aviation Administration, Office of Aviation Research ;, 1996), by M. L. Gruber, Boeing Company. Commercial Airplane Group, and United States. Federal Aviation Administration. Office of Aviation Research (page images at HathiTrust)
• Drag measurements of upswept afterbodies and analytical study on axisymmetric separation (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by Mansop Hahn, Theodore C. Nark, Paul E. Rubbert, Gunter W. Brune, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Commercial Airplane Company (page images at HathiTrust)
• Method of determining reduction in elevator effectiveness when engine is mounted on aft fuselage of aircraft (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1961., 1961), by James R. Atchison, Air Force Flight Dynamics Laboratory (U.S.), United States. Air Force. Systems Command, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Evaluation of the twin nozzle/afterbody drag and nozzle internal performance computer deck with ESIT free jet data (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, 1974., 1974), by Phillip C. Everling, Douglas L. Bowers, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Heterogeneous construction for missile fuselages (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Adam T. Zahorski, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Inc Zahorski Engineering (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)
• Influence of forebody geometry on aerodynamic characteristics and a design guide for defining departure/spin resistant forebody configurations (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Wright Research and Development Center, Air Force Systems Command, United States Air Force, 1989., 1989), by William Bihrle, E. Dickes, B. Barnhart, Inc Bihrle Applied Research, Wright Research and Development Center, Air Force Flight Dynamics Laboratory (U.S.), and United States. Air Force. Systems Command (page images at HathiTrust)
• Computation of axisymmetric separated nozzle-afterbody flow (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1980., 1980), by James L. Jacocks, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Quantifying the effect of fuselage cross-sectional shape on structural weight (Wright-Patterson Air Force Base, Ohio : Air Force Research Laboratory, Air Force Materiel Command, 2007., 2007), by Michael A. Falugi, Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base, and United States. Air Force Materiel Command (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)
• Afterbody drag investigation of a twin-nozzle fighter-type model at Mach numbers from 0.6 to 1.5 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by Earl A. Price, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Experimental method for correcting nozzle afterbody drag for the effects of jet temperature (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by W. L. Peters, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (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)
• Static and rotational aerodynamic data from O° to 90° angle of attack for a series of basic and altered forebody shapes (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Wright Research and Development Center, Air Force Systems Command, United States Air Force, 1989., 1989), by William Bihrle, E. Dickes, B. Barnhart, Inc Bihrle Applied Research, Wright Research and Development Center, Air Force Flight Dynamics Laboratory (U.S.), 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)
• Simplified input for certain aerodynamic nose configurations to the Grumman QUICK-geometry system : a KWIKNOSE User's Manual (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by Frederick L. Shope, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Two-component simultaneous LDV (Laser Doppler Velocimeter) turbulence measurements in an axisymmetric nozzle afterbody subsonic flow field with a cold, underexpanded supersonic jet (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1983., 1983), by F. L. Heltsley, F. L. Crosswy, Calspan Field Services, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• A method for estimating jet entrainment effects on nozzle-afterbody drag (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1980., 1980), by R. C. Bauer, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Experimental definition of top mounted inlet flow fields : Volume I (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1979., 1979), by William W. Rhoades, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and Vought Corporation (page images at HathiTrust)

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