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- Effects of spanwise location of sweep discontinuity on the low-speed static lateral stability characteristics of a complete model with wings of M and W plan form
- A method for evaluating the loads and controllability aspects of the pitch-up problem
- Application of non-afterburning turbojets to supersonic flight
- Application of statistical theory to beam-rider guidance in the presence of noise 1: Wiener filter theory
- Application of wing-body theory to drag reduction at low supersonic speeds
- Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 2
- Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98
- Wind-tunnel investigation at Mach 1.9 of multijet-missile base pressures
- Performance of four experimental high btu-per-gallon fuels in a single turbojet combustor
- Performance of a supersonic compressor with swept and tilted diffuser blades
- Matching of auxiliary inlets to secondary-air requirements of aircraft ejector exhaust nozzles
- Some design implications of the effects of aerodynamic heating
- Spark ignition of flowing gases 5: application of fuel-air-ratio and initial-temperature data to ignition theory
- A special method for finding body distortions that reduce the wave drag of wing and body combinations at supersonic speeds
- Panel-flutter investigation at supersonic speeds of a pressurized structure fabricated of 0.020-inch-thick laminated glass-plastic
- Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines 4: coolant-flow requirements and performance of engines using air-cooled corrugated-insert blades
- Analytical comparison of convection-cooled turbine blade cooling-air requirements for several radial gas-temperature profiles
- Wind-tunnel investigation at low speed of a wing having 63 degree sweepback and a drooped tip
- Performance characteristics of axisymmetric two-cone and isentropic nose inlets at Mach number 1.90
- A variable-geometry axisymmetric supersonic inlet with telescoping centerbody
- Downwash survey behind two low-aspect-ratio variable-incidence wings in combination with three different size fuselages at a Mach number of 0.25
- Theoretical analysis of the longitudinal behavior of an automatically controlled supersonic interceptor during the attack phase
- Effect of leading-edge sweepback on lift, drag, and pitching-moment characteristics of thin wings of aspect ratio 3 and taper ratio 0.4 at subsonic and supersonic speeds
- A study of conical camber for triangular and sweptback wings
- Investigation of effectiveness of large-chord slotted flaps in deflecting propeller slipstreams downward for vertical take-off and low-speed flight
- Analysis of Low-Temperature Nuclear-Powered Ram-Jet Missile for High Altitudes
- Lift, drag, and longitudinal stability at Mach numbers from 1.4 to 2.3 of a rocket-powered model having a 52.5 degree sweptback wing of aspect ratio 3 and inline tail surfaces
- Transportation of liquid fluorine
- Model investigation of the effect of mounting hydro-skis on shock absorbers
- Lift, drag, and longitudinal stability at Mach numbers from 0.8 to 2.1 of a rocket-powered model having a tapered unswept wing of aspect ratio 3 and inline tail surfaces
- Performance characteristics of hemispherical target-type thrust reversers
- Performance of YJ73-GE-3 turbojet engine in altitude test chamber
- Investigation at high subsonic speeds of the effects of various underwing external-store arrangements on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II Research Airplane
- An investigation at high subsonic speeds of the effects of horizontal-tail height on the aerodynamic and loading characteristics in sideslip on a 45 degree sweptback, untapered tail assembly as determined from force tests and integrated vertical-tail span loadings
- The effect of fluid injection on the compressible turbulent boundary layer : preliminary tests on transpiration cooling of a flat plate
- Effect of fuselage fences on the angle-of-attack supersonic performance of a top-inlet-fuselage configuration
- A theoretical analysis of the effect of engine angular momentum on longitudinal and directional stability in steady rolling maneuvers
- An experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface
- Gust-load and airspeed data from one type of four-engine airplane on five routes from 1947 to 1954
- Free-flight investigation to determine some effects of tail damping and wing-tail interference on the rolling effectiveness of inboard and outboard ailerons on an untapered sweptback wing
- Free-flight investigation, including some effects of wing aeroelasticity, of the rolling effectiveness of an all-movable horizontal tail with differential incidence at Mach numbers from 0.6 to 1.5
- Effects of leading-edge radius on the longitudinal stability of two 45 degree sweptback wings as influenced by Reynolds numbers up to 8.20 x 10(exp 6) and Mach numbers up to 0.303
- Development of a new flutter testing technique using a towed dynamic airplane model equipped with an automatic stabilizing system: Experimental and calculated dynamic stability characteristics for speeds up to 200 mph
- A survey of unclassified axial-flow-compressor literature
- Flight measurements of the vertical-tail loads on the Convair XF-92A delta-wing airplane
- Effects of sweep and taper on the longitudinal characteristics of an aspect ratio 3 wing-body combination at Mach numbers from 0.6 to 1.4
- A method for simulating the atmospheric entry of long-range ballistic missiles
- Flight Determination of the Longitudinal Stability and Control Characteristics of a 0.125-Scale Rocket-Boosted Model of the Mcdonnell F-101 Airplane at Mach Numbers from 0.82 to 1.84
- An investigation of string support interference on base pressure and forebody chord force at Mach numbers from 0.60 to 1.30
- Collection and summary of flap-type-aileron rolling-effectiveness data at zero lift as determined by rocket-powered model tests at Mach numbers between 0.6 and 1.6