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- Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61
- Effects of high-lift and stall-control devices, fuselage, and horizontal tail on a wing swept back 42 degrees at the leading edge and having symmetrical circular-arc airfoils sections at a Reynolds number of 6.9 x 10(exp 6)
- Experimental performance of chlorine trifluoride-hydrazine propellant combination in 100-pound-thrust rocket engine
- Flight investigation of the effect of boundary-layer suction on profile-drag coefficient at supercritical Mach numbers
- Turbine-rotor-blade designs based on one-dimensional-flow theory I : performance of single-stage turbine having 40-percent reaction
- Altitude-chamber performance of British Rolls-Royce Nene II engine I : standard 18.75-inch-diameter jet nozzle
- Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees
- Wind-Tunnel investigation of NACA 65,3-418 airfoil section with boundary-layer control through a single suction slot applied to a plain flap
- Altitude performance of AN-F-58 fuels in J33-A-21 single combustor
- Altitude-wind-tunnel investigation of compressor performance on J47 turbojet engine
- Altitude-wind-tunnel investigation of AN-F-58 fuel in experimental version of J47 turbojet engine
- Two-dimensional aerodynamic characteristics of 34 miscellaneous airfoil sections
- Two-dimensional wind-tunnel investigation of a 6-percent-thick symmetrical circular-arc airfoil section with leading-edge and trailing-edge high-lift devices deflected in combination
- Two-dimensional wind tunnel investigation of a symmetrical airfoil section with a sealed internally balanced control surface and a leading tab
- Low-speed pressure-distribution and flow investigation for a large pitch and yaw range of three low-aspect-ratio pointed wings having leading edge swept back 60 degrees and biconvex sections
- Low-speed static longitudinal stability characteristics of a canard model having a 60 degrees triangular wing and horizontal tail
- Low-speed static-stability and rolling characteristics of low-aspect-ratio wings of triangular and modified triangular plan forms
- Low-speed wind-tunnel investigation of the longitudinal stability characteristics of a model equipped with a variable-sweep wing
- Stability and Control Data Obtained from Fourth and Fifth Flights of the Northrop X-4 Airplane (A.F. No. 46-676)
- High-subsonic damping-in-roll characteristics of a wing with the quarter-chord line swept back 35 degrees and with aspect ratio 3 and taper ratio 0.6
- Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle
- Effect of temperature on performance of several ejector configurations
- An empirical criterion for fin stabilizing jettisonable nose sections of airplanes
- Experimental determination of the subsonic performance of a ram-jet unit containing thin-plate burners
- Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25
- Experimental investigation of liquid diborane - liquid oxygen propellant combination in 100-pound-thrust rocket engine
- Analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters
- Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 2: nacelle with long straight air inlet
- Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 3: nacelle with short straight air inlet
- Experimental investigation at supersonic speeds of side scoops employing boundary-layer suction
- Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area IV : some effects of internal duct shape upon an inlet enclosing 37.2 percent of the forebody circumference
- Effects of wing-tip turrets on the aerodynamic characteristics of a typical bomber-wing model
- Experimental pressure distribution on a asymmetrical nonconical body at Mach number 1.90
- Reynolds number effect on axial-flow compressor performance
- Investigation of the NACA 4-(5)(08)-03 Two-Blade Propeller at Forward Mach Numbers to 0.925
- Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine
- A comparison of the experimental subsonic pressure distributions about several bodies of revolution with pressure distributions computed by means of the linearized theory
- Cyclic engine operation of cast vitallium turbine blades at an exhaust-cone gas temperature of 1440 plus or minus 20 F
- Investigation of downwash and wake characteristics at a Mach number of 1.53 2: triangular wing
- Investigation of downwash and wake characteristics at a Mach number of 1.53 1: rectangular wing
- Wind-tunnel investigation of a tailless triangular-wing fighter aircraft at Mach numbers from 0.5 to 1.5
- Wind-tunnel investigation of horizontal tails. 5: 45 degree swept-back plan form of aspect ratio 2
- Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge
- Calculative method for estimating the interference pressure field at zero lift on a symmetrical swept-back wing mounted on a circular cylindrical body
- Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Effects of split flaps, elevons, and leading-edge devices at low speed
- Vibration of loosely mounted turbine blades during service operation of a turbojet engine with centrifugal compressor and straight-flow combustion chambers
- Model ditching investigation of the Douglas DC-4 and DC-6 airplanes
- Free-flight performance of 16-inch-diameter supersonic ram-jet units 1: four units designed for combustion-chamber-inlet Mach number of 0.12 at free-stream Mach number of 1.6 (units A-2, A-3, A-4, and A-5)
- Investigation at large scale of the pressure distribution and flow phenomena over a wing with the leading edge swept back 47.5 degrees having circular-arc airfoil sections and equipped with drooped-nose and plain flaps
- A comparison of theoretical and experimental loading on a 63 degrees swept-back wing at supersonic speeds