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Stability of airplanes, Longitudinal

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Airplanes -- Longitudinal stability
Longitudinal stability of airplanes

Filed under: Stability of airplanes, Longitudinal

Flight evaluation of various phugoid dynamics and 1/Th values for the landing-approach task. (Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1966), by Charles R. Chalk and Cornell Aeronautical Laboratory (page images at HathiTrust)
A feasibility study of self-learning adaptive flight control for high performance aircraft (Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1967), by Stephen G. Hoppe, Claron W. Swonger, and Semmelhack Henry P. (page images at HathiTrust)
A systems analysis view of longitudinal flying qualities (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, U.S. Air Force, 1960., 1960), by Duane T. McRuer, C. L. Guerre, Irving L. Ashkenas, United States. Wright Air Development Division, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
Subsonic longitudinal and lateral-directional characteristics of a forward-swept-wing fighter configuration at angles of attack up to 47⁰ (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Michael J. Mann, Charles H. Fox, Jarrett K. Huffman, and Langley Research Center (page images at HathiTrust)
Longitudinal stability and control characteristics of the Quiet Short-Haul Research Aircraft (QSRA) (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Jack D. Stephenson, Gordon H. Hardy, and Ames Research Center (page images at HathiTrust)
Simulator study of stall/post-stall characteristics of a fighter airplane with longitudinal static stability (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Luat T. Nguyen, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Total energy-rate feedback for automatic glide-slope tracking during wind-shear penetration (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Christine M. Belcastro, Aaron J. Ostroff, and Langley Research Center (page images at HathiTrust)
Effects of upper-surface nacelles on longitudinal aerodynamic characteristics of high-wing transport configuration (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Lawrence E. Putnam and Langley Research Center (page images at HathiTrust)
Effects of external stores on the aerodynamic characteristics of a 60 ̊Delta-wing fighter model at mach 1.60 to 2.87 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by M. Leroy Spearman, William J. Monta, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Effect of under-wing aft-mounted nacelles on the longitudinal aerodynamic characteristics of a high-wing transport airplane (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William Kelly Abeyounis, James C. Patterson, and Langley Research Center (page images at HathiTrust)
Simulator evaluation of the effects of reduced spoiler and thrust authority on a decoupled longitudinal control system during landings in wind shear (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by G. Kimball Miller, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Analysis of oscillatory motion of a light airplane at high values of lift coefficient (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by James G. Batterson, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Effects of deflected thrust on the longitudinal aerodynamic chartacteristics of a close-coupled wing-canard configuration (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Long P. Yip, John W. Paulson, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Longitudinal aerodynamic characteristics of a deflected-thrust propulsive-lift transport model (National Aeronautics and Space Administration ;, 1975), by Danny R. Hoad and Langley Research Center (page images at HathiTrust)
Piloted simulator study of allowable time delay in pitch flight control system of a transport airplane with negative static stability (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by William D. Grantham and Langley Research Center (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)
Theoretical and experimental investigation of ground-induced effects for a low-aspect-ratio highly swept arrow-wing configuration (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Paul L. Coe, James L. Thomas, Langley Research Center, 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)
The effect of the converging flow field of a tandem-test-section on longitudinal stability measurements (National Aeronautics and Space Administration, 1968), by Shojiro Shindo and Robert G. Joppa (page images at HathiTrust)
Turbulence and longitudinal flying qualities (For sale by the National Technical Information Service, 1971), by James A. Franklin, United States National Aeronautics and Space Administration, and Princeton University (page images at HathiTrust)
A Design study for a simple-to-fly, constant attitude light aircraft (National Aeronautics and Space Administration ;, 1973), by Frederick O. Smetana, Langley Research Center, and North Carolina State University (page images at HathiTrust)
Theoretical analysis of the longitudinal behavior of an automatically controlled supersonic interceptor during the attack phase (Langley Research Center ;, 1959), by Ordway B. Gates and United States National Aeronautics and Space Administration (page images at HathiTrust)
Summary and analysis of horizontal-tail contribution to longitudinal stability of swept-wing airplanes at low speeds (U.S. G.P.O.], 1959), by Robert H. Neely (page images at HathiTrust)
Effect of wing planform and canard location and geometry on the longitudinal aerodynamic characteristics of a close-coupled canard wing model at subsonic speeds (National Aeronautics and Space Administration ;, 1975), by Blair B. Gloss and Langley Research Center (page images at HathiTrust)
Analysis of longitudinal pilot-induced oscillation tendencies of YF-12 aircraft (National Aeronautics and Space Administration, 1975), by Flight Research Center (U.S.), Donald T. Berry, and John W. Smith (page images at HathiTrust)
Calculation of the dynamic longitudinal stability of a tilt-wing V/STOL aircraft and correlation with model flight tests (National Aeronautics and Space Administration, 1968), by Joseph R. Chambers, Sue B. Grafton, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Static longitudinal characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations (National Aeronautics and Space Administration, 1961), by Kenneth W. Goodson, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Effect of canard leading-edge sweep and dihedral angle on the longitudinal and lateral aerodynamic characteristics of a close-coupled canard-wing configuration (National Aeronautics and Space Administration ;, 1974), by Blair B. Gloss and Langley Research Center (page images at HathiTrust)
Effects of nozzle interfairing modifications on longitudinal aerodynamic characteristics of a twin-jet, variable-wing-sweep fighter model (National Aeronautics and Space Administration ;, 1975), by David E. Reubush, Charles E. Mercer, and Langley Research Center (page images at HathiTrust)
An analytical study and wind-tunnel tests of an aeromechanical gust-alleviation system for a light airplane (National Aeronautics and Space Administration ;, 1976), by Eric C. Stewart (page images at HathiTrust)
NASA TN D-6142 (National Aeronautics and Space Administration ;, 1971), by Richard J. Margason, John E. Lamar, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
NASA TN D-5857 (National Aeronautics and Space Administration ;, 1970), by James P. Shivers, George M. Ware, Marvin P. Fink, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Theoretical and experimental analysis of longitudinal and lateral aerodynamic characteristics of skewed wings at subsonic speeds to high angles of attack (National Aeronautics and Space Administration ;, 1977), by James M. Luckring and United States National Aeronautics and Space Administration (page images at HathiTrust)
A theoretical analysis of airplane longitudinal stability and control as affected by wind shear (National Aeronautics and Space Administration ;, 1977), by Windsor L. Sherman, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Low-speed wind-tunnel tests of 1/10-scale model of a blended-arrow supersonic cruise aircraft (National Aeronautics and Space Administration ;, 1977), by H. Clyde McLemore, Lysle P. Parlett, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Effects of body shape on the aerodynamic characteristics of an all-body hypersonic aircraft configuration at Mach numbers from 0.65 to 10.6 (National Aeronautics and Space Administration ;, 1972), by Walter P. Nelms and Ames Research Center (page images at HathiTrust)
Study of the optimum values of several parameters affecting longitudinal handling qualities of VTOL aircraft (National Aeronautics and Space Administration, 1968), by James R. Kelly, John F. Garren, Langley Research Center, and United States National Aeronautics and Space Administration (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)
Wind-tunnel investigation of static longitudinal and lateral characteristics of a full-scale mockup of a light single-engine high-wing airplane (National Aeronautics and Space Administration ;, 1973), by H. Douglas Greer and Langley Research Center (page images at HathiTrust)
Static and dynamic longitudinal stability derivatives of a powered 0.18 scale model of a fan-in-wing VTOL aircraft (National Aeronautics and Space Administration, 1968), by Joseph R. Chambers, Sue B. Grafton, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Aerodynamic characteristics of a three-engine supersonic transport model having a low-aspect-ratio variable-sweep warped wing (National Aeronautics and Space Administration, 1964), by Odell A. Morris, Dennis E. Fuller, and Langley Research Center (page images at HathiTrust)
Effect of wing pivot location on longitudinal aerodynamic characteristics of a variable-sweep wing having an M planform (National Aeronautics and Space Administration, 1964), by William P. Henderson, Edward J. Ray, and Langley Research Center (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)
Investigation of the aerodynamic characteristics of a supersonic horizontal- attitude VTOL airplane model at Mach numbers of 1.57, 2.14, 2.54, and 2.87 (National Aeronautics and Space Administration, 1960), by Arthur E. Franklin, Robert M. Lust, and Langley Research Center (page images at HathiTrust)
Aerodynamic characteristics of a tailless fixed-wing supersonic transport configuration at Mach number 2.20 (National Aeronautics and Space Administration, 1964), by Gerald V. Foster, William A. Corlett, and Langley Research Center (page images at HathiTrust)
Investigation of the static stability characteristics of a reentry spacecraft model in free flight for Mach numbers from 2.62 to 1.11 launched at an angle of attack of 180 degree (National Aeronautics and Space Administration, 1961), by J. W. Usry and Langley Research Center (page images at HathiTrust)
Low-speed investigation of the aerodynamic characteristics of a variable-sweep supersonic transport configuration having a blended wing and body (National Aeronautics and Space Administration, 1961), by William C. Sleeman, A. Warner Robins, and Langley Research Center (page images at HathiTrust)
Static longitudinal and lateral aerodynamic characteristics at a Mach number of 2.01 of a tailless delta V/STOL configuration having variable-sweep wing panels (National Aeronautics and Space Administration, 1961), by M. Leroy Spearman, Gerald V. Foster, and Langley Research Center (page images at HathiTrust)
Longitudinal stability and control derivatives of a jet fighter airplane extracted from flight test data by utilizing maximum likelihood estimation (National Aeronautics and Space Administration, 1971), by George G. Steinmetz, Russell V. Parrish, Roland L. Bowles, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
NASA TN D-6430 (National Aeronautics and Space Administration ;, 1971), by Joseph Gera, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-36 (National Aeronautics and Space Administration :, 1966), by Victor R. Corsiglia, David G. Koenig, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-4083 (National Aeronautics and Space Administration ;, 1967), by Raymond D. Vogler, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-1774 (National Aeronautics and Space Administration, 1963), by Kenneth W. Mort, Paul F. Yaggy, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Extraction of longitudinal aerodynamic coefficients from forward-flight conditions of a tilt wing V/STOL airplane (National Aeronautics and Space Administration ;, 1972), by James L. Williams, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
The static stability characteristics of several preliminary models of the X-15 research airplane at Mach numbers of 2.98 and 4.01 (National Aeronautics and Space Administration, 1959), by Robert W. Dunning, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Effects of wing planform on the aerodynamic characteristics of a wing-body-tail model at Mach numbers 1.57, 2.16, and 2.87 (National Aeronautics and Space Administration :, 1965), by Royce L. McKinney, Lloyd S. Jernell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Wind-tunnel investigation of a large-scale semispan model with an unswept wing and an upper-surface blown jet flap (National Aeronautics and Space Administration ;, 1974), by Charles Christian Smith, W. Latham Copeland, Arthur E. Phelps, and Langley Research Center (page images at HathiTrust)
Longitudinal and lateral stability characteristics of two four-jet vtol models in the transition speed range (National Aeronautics and Space Administration, 1965), by Raymond D. Vogler, Richard E. Kuhn, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Longitudinal aerodynamic characteristics of an externally blown flap powered-lift model with several propulsive system simulators (National Aeronautics and Space Administration ;, 1974), by Danny R. Hoad and Langley Research Center (page images at HathiTrust)
Simulator study of minimum acceptable level of longitudinal stability for a representative STOL configuration during landing approach (National Aeronautics and Space Administration ;, 1974), by William D. Grantham, Perry L. Deal, and Langley Research Center (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1946), by Paul A. Hunter, John P. Reeder, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by John P. Campbell, John W. Paulson, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Low-speed effects of high-lift devices on the aerodynamic characteristics of a supersonic transport model with outboard tails (National Aeronautics and Space Administration, 1963), by William C. Sleeman, Paul G. Fournier, Edward J. Ray, and Langley Research Center (page images at HathiTrust)
Longitudinal aerodynamic characteristics at transonic speeds of a V/STOL airplane configuration with a fixed delta wing having auxiliary variable-sweep outboard panels (National Aeronautics and Space Administration, 1961), by Arvo A. Luoma and Langley Research Center (page images at HathiTrust)
Low-speed investigation of effects of vertical tails on the static stability characteristics of a canard-bomber configuration having a very thin wing and a slender elliptical fuselage (National Aeronautics and Space Administration, 1961), by Thomas G. Gainer and Langley Research Center (page images at HathiTrust)
Measurements of the surface flows, heat transfer, pressure distribution, and longitudinal stability of a mercury capsule model at Mach numbers of 6.9 and 9.6 (National Aeronautics and Space Administration, 1961), by Philip E. Everhart, Peter T. Bernot, and Langley Research Center (page images at HathiTrust)
Investigation of the static longitudinal stability and roll characteristics of a three-stage missile configuration at mach numbers from 1.77 to 2.87 (National Aeronautics and Space Administration, 1959), by Donald T. Gregory, Ausley B. Carraway, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and cambered fuselage (National Aeronautics and Space Administration ;, 1974), by Samuel M. Dollyhigh and Langley Research Center (page images at HathiTrust)
Static investigation of several jet deflectors for longitudinal control of an aircraft (National Advisory Committee for Aeronautics, 1955), by Alfred S. Valerino, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Measurement of the longitudinal moment of inertia of a flexible airplane (National Advisory Committee for Aeronautics, 1956), by Henry Ambrose Jr Cole, Frances L. Bennion, United States National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
Longitudinal aerodynamic characteristics of a model airplane configuration equipped with a scaled X-1 airplane wing (National Advisory Committee for Aeronautics, 1952), by James H. Parks, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Longitudinal stability characteristics at transonic speeds of a rocket-propelled model of an airplane having a 45 degree swept wing of aspect ratio 6.0 (National Advisory Committee for Aeronautics, 1954), by John C. McFall, 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)
Longitudinal stability and trim of two rocket-propelled airplane models having 45©� sweptback wings and tails with the horizontal tail mounted in two positions (National Advisory Committee for Aeronautics, 1953), by James H. Parks, Alan B. Kehlet, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Analog-computer investigation of effects of friction and preload on the dynamic longitudinal characteristics of a pilot-airplane combination. (National Advisory Committee for Aeronautics, 1957), by Harold L. Crane, Langley Aeronautical Laboratory, and United States. National Adviosry 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)
An investigation at Mach numbers 1.94 and 2.41 of jet effects upon the longitudinal and directional stability of a general aircraft configuration employing wing-tip-mounted nacelles (National Advisory Committee for Aeronautics, 1958), by Frank L. Clark, C. L. W. Edwards, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Some effects of fin plan form on the static stability of fin-body combinations at Mach number 4.06 (National Advisory Committee for Aeronautics, 1952), by Edward F. Ulmann, Robert W. Dunning, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Transonic wind-tunnel investigation of the interference between a 45©� sweptback wing and a systematic series of four bodies (National Advisory Committee for Aeronautics, 1952), by Donald L. Loving, Dewey E. Wornom, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Effects of twist and camber on the low-speed longitudinal stability characteristics of a 45©� swept-back wing of aspect ratio 8 at Reynolds numbers from 1.5 x 10⁶ to 4.8 x 10 as determined by pressure distributions, force tests, and calculations (National Advisory Committee for Aeronautics, 1952), by George L. Pratt, 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)
Some effects of tail height and wing plan form on the static longitudinal stability characteristics of a small-scale model at high subsonic speeds (National Advisory Committee for Aeronautics, 1954), by Albert G. Few, Thomas J. King, 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, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
The static and dynamic longitudinal stability characteristics of some supersonic aircraft configurations (National Advisory Committee for Aeronautics, 1952), by Jesse L. Mitchell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Longitudinal stability and control characteristics from a flight investigation of a cruciform canard missile configuration having an exposed wing-canard area ratio of 16:1 (National Advisory Committee for Aeronautics, 1952), by Martin T. Moul, Andrew R. Wineman, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Low-speed pitching derivatives of low-aspect-ratio wings of triangular and modified triangular plan forms (National Advisory Committee for Aeronautics, 1950), by Alex Goodman, Byron M. Jaquet, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Damping-in-pitch characteristics at high subsonic and transonic speeds of four 35©� sweptback wings (National Advisory Committee for Aeronautics, 1953), by William B. Kemp, Robert E. Becht, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Some low-speed wind-tunnel experiments pertaining to the longitudinal stability characteristics of a 35©� swept-wing model and an unswept-wing model (National Advisory Committee for Aeronautics, 1953), by Byron M. Jaquet, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Three-degree-of-freedom evaluation of the longitudinal transfer functions of a supersonic canard missile configuration including changes in forward speed (National Advisory Committee for Aeronautics, 1954), by Ernest C. Seaberg, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Aerodynamic characteristics at small scale and a Mach number of 1.38 of untapered wings having M and W plan forms (National Advisory Committee for Aeronautics, 1954), by William B. Kemp, 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)
Lift, drag, and static longitudinal stability data from an exploratory investigation at a Mach number of 6.86 of an airplane configuration having a wing of trapezoidal plan form (National Advisory Committee for Aeronautics, 1955), by Jim A. Penland, David E. Fetterman, Herbert W. Ridyard, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Preliminary results for a free-flight investigation at transonic and supersonic speeds of longitudinal stability and control characteristics of an airplane configuration with a thin straight wing of aspect ratio 3 (National Advisory Committee for Aeronautics, 1950), by Clarence L. Gillis, A. James Vitale, Robert F. Peck, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Matrix method of determining the longitudinal-stability coefficients and frequency response of an aircraft from transient flight data (National Advisory Committee for Aeronautics, 1951), by James J. Donegan, H. A. Pearson, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of horizontal-tail location on low-speed static longitudinal stability and damping in pitch of a model having 45©� sweptback wing and tail surfaces (National Advisory Committee for Aeronautics, 1951), by Jacob H. Lichtenstein and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of horizontal-tail size and tail length on low-speed static longitudinal stability and damping in pitch of a model having 45©� sweptback wing and tail surfaces (National Advisory Committee for Aeronautics, 1951), by Jacob H. Lichtenstein and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Charts and approximate formulas for the estimation of aeroelastic effects on the loading of swept and unswept wings (National Advisory Committee for Aeronautics, 1952), by Franklin W. Diederich, Kenneth A. Foss, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Static longitudinal stability characteristics of a blunted glider reentry configuration having 79.5° sweepback and 45° dihedral at mach number of 6.2 and angles of attack up to 20° (National Aeronautics and Space Administration, 1959), by Edward E. Mayo and United States National Aeronautics and Space Administration (page images at HathiTrust)
Hypersonic longitudinal trim, stability, and control characteristics of a delta-wing configuration at high angles of attack (National Aeronautics and Space Administration, 1960), by William H. Close 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)
Static stability characteristics of three thick wing models with parabolic plan forms at mach number of 3.11 (National Aeronautics and Space Administration, 1959), by M. J. Queijo and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Effects of wing-crank, leading-edge chord extensions and horizontal-tail height on the longitudinal stability of swept-wing models at mach numbers from 0.6 to 1.4 (National Aeronautics and Space Administration, 1959), by Roy M. Wakefield and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
The effects of wing plan form on the static longitudinal aerodynamic characteristics of a flat-top hypersonic aircraft at Mach numbers from 0.6 to 1.4 (National Aeronautics and Space Administration, 1960), by Stuart L. Treon, Ames 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)
Low-speed static longitudinal and lateral stability characteristics of a variable-incidence delta-wing canard model with high-lift canard surfaces (National Aeronautics and Space Administration, 1959), by Clarence D. Cone and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Static stability characteristics of a series of hypersonic boost-glide configurations at mach numbers of 1.41 and 2.01 (National Aeronautics and Space Administration, 1959), by Gerald V. Foster and United States National Aeronautics and Space Administration (page images at HathiTrust)
Aerodynamic characteristics at mach numbers of 1.41 and 2.01 of a series of cranked wings ranging in aspect ratio from 4.00 to 1.74 in combination with a body (National Aeronautics and Space Administration, 1960), by John R. Sevier and United States National Aeronautics and Space Administration (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, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Some effects of aircraft configuration on static longitudinal and directional stability characteristics at supersonic Mach numbers below 3 (National Advisory Committee for Aeronautics, 1959), by M. Leroy Spearman, Arthur Henderson, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Wind-tunnel investigation of the static longitudinal and lateral stability of a 1/62-scale model of the X-1E at supersonic speeds (National Advisory Committee for Aeronautics, 1956), by Arthur Henderson and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effects of wing-tip droop on the longitudinal characteristics of two highly swept wing-body combinations at Mach numbers from 0.6 to 1.4 (National Advisory Committee for Aeronautics, 1957), by Earl D. Knechtel, George Lee, Ames Research Center, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series A. (National Advisory Committee for Aeronautics, 1945), by William N. Turner, Lawrence A. Clousing, Paul J. Steffen, Ames Research Center, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1942), by John G. Lowry, Thomas A. Toll, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Rocket-model investigation of longitudinal stability and drag characteristics of an airplane configuration have a 60©� delta wing and a high unwept horizontal tail (Washington, D.C. : National Advisory Committee for Aeronautics, 1953, 1953), by Robert F. Peck, Jesse L. Mitchell, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Jet effects on longitudinal trim of an airplane configuration measured at Mach numbers between 1.2 and 1.8 (Washington, D.C. : National Advisory Committee for Aeronautics, 1955., 1955), by Robert F. Peck, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
A transonic wind-tunnel investigation of the longitudinal force and moment characteristics of two delta wings and one clipped-tip delta wing of 4 percent thickness on a slender body (Washington, D.C. : National Advisory Committee for Aeronautics, 1955., 1955), by William E. Palmer, Dale L. Burrows, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Longitudinal airplane dynamics wind tunnel test equipment (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1955., 1955), by O. B. Tufts, A. H. Zimmerman, R. C. MacArthur, G. R. Duryea, Wright Air Development Center, United States. Air Force. Air Research and Development Command, and Cornell Aeronautical Laboratory (page images at HathiTrust)
Flight evaluation of various short period dynamics at four drag configurations for the landing approach task (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by Charles R. Chalk, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Cornell Aeronautical Laboratory (page images at HathiTrust)
Longitudinal static stability and inlet drag characteristics of the McDonnell Douglas F-15 tactical fighter aircraft at Mach numbers of 1.60 and 2.20 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1971., 1971), by F. J. Keeney, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Non-linear effects in the longitudinal dynamics of a lifting vehicle in a circular orbit (Toronto, Canada : University of Toronto, Institute of Aerophysics, 1960., 1961), by R. S. Rangi, University of Toronto. Institute of Aerophysics, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
The determination of aircraft stability coefficients from flight-test data : Part 2 : Longitudinal investigations (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by L. E. Wilkie, Meredith N. Springer, 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)
Simulator evaluation of airplane longitudinal responses for the instrument-landing approach. (AF Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1964), by F. D. Newell and Cornell Aeronautical Laboratory (page images at HathiTrust)

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