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- Stability of bodies of revolution having fineness ratios smaller than 1.0 and having rounded fronts and blunt bases
- Air-flow and thrust characteristics of several cylindrical cooling-air ejectors with a primary to secondary temperature ratio of 1.0
- Influence of end plates on lift and flow field of a canard-type control surface at a Mach number of 2.00
- Hinge-moment characteristics for several tip controls on a 60 degree sweptback delta wing at Mach number 1.61
- Effect of inlet oxygen concentration on combustion efficiency of J33 single combustor operating with gaseous propane
- Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with bypasses discharging in an axial direction
- Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with a bypass discharging from the top or bottom of the diffuser in an axial direction
- Forced-convection heat-transfer characteristics of molten sodium hydroxide
- Altitude wind tunnel investigation of the prototype J40-WE-8 turbojet engine without afterburner
- Considerations in the adaptation of low-cost fuels to gas-turbine-powered commercial aircraft
- Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) III : boundary layer and force measurements on a slender cone-cylinder body of revolution
- Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics : effect of compressor interstage air bleed
- Experimental investigation of an axial-flow supersonic compressor having rounded leading-edge blades with an 8-percent mean thickness-chord ratio
- Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers III : blade-row performance of stage with transonic rotor and subsonic stator at corrected tip speeds of 800 and 1000 feet per secon
- Investigation at a Mach number of 1.90 of a diverter-type boundary-layer removal system for a scoop inlet
- De-icing and runback characteristics of three cyclic electric, external de-icing boots employing chordwise shedding
- A method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow
- Investigation at Mach numbers 1.5 and 1.7 of twin-duct side air-intake system with 9 degree compression ramp including modifications to boundary-layer-removal wedges and effects of a bypass system
- Preliminary investigation of the effect of fences and balancing tabs on the hinge-moment characteristics of a tip control on a 60 degree delta wing at Mach number 1.61
- Preliminary investigation of the effects of body contouring as specified by the transonic area rule on the aerodynamic characteristics of a delta wing-body combination at Mach numbers of 1.41 and 2.01
- The low-speed lift and pitching moment characteristics of a 45 degree sweptback wing of aspect ratio 8 with and without high-lift and stall-control devices as determined from pressure distribution at a Reynolds number of 4.0 x 10(exp 6)
- A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds
- Some effects of frequency on the contribution of a vertical tail to the free aerodynamic damping of a model oscillating in yaw
- Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude II : air-cooling systems
- Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude I : liquid-cooling systems
- An analysis of the tracking performances of two straight-wing and two swept-wing fighter airplanes with fixed sights in a standardized test maneuver
- Analysis of the turbojet engine for propulsion of supersonic fighter airplanes
- Analysis of turbine stator adjustment required for compressor design-point operation in high Mach number supersonic turbojet engines
- Wing loads on the Bell X-1 research airplane (10 percent thick wing) as determined by pressure-distribution measurements in flight at subsonic and transonic speeds
- Wind-tunnel investigation of the behavior of parachutes in close proximity to one another
- Wind-tunnel investigation of the vortex wake and downwash field behind triangular wings and wing-body combinations at supersonic speeds
- Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees
- An experimental investigation at subsonic and supersonic speeds of the torsional damping characteristics of a constant-chord control surface of an aspect ratio 2 triangular wing
- Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers I : rotor design and over-all performance at tip speeds from 60 to 100 percent of design
- Effects of rate of flap deflection on flap hinge moment and wing lift through the Mach number range from 0.32 to 0.87
- Free-flight performance of a rocket-boosted, air-launched 16-inch-diameter ram-jet engine at Mach numbers up to 2.20
- Free-flight tests of three 1/9-scale models of the wing-ram-jet configuration of the Grumman XSSM-N-6A (Rigel) missile to investigate the possibility of flutter : TED No. NACA DE 223
- Free-flight-tunnel investigation of the low-speed stability and control characteristics of a canard airplane model
- Free-flight longitudinal-stability investigation including some effects of wing elasticity from Mach numbers of 0.85 to 1.34 of a tailless missile configuration having a 45 degree sweptback wing of aspect ratio 5.5
- Ignition delays of some nonaromatic fuels with low-freezing red fuming nitric acid in temperature range -40 to -105 degrees F
- Internal performance characteristics of variable-throat plug- and vaned-type convergent-divergent nozzles
- Effect of axially staged fuel introduction on performance of one-quarter sector of annular turbojet combustor
- Comparison of pressure-loss characteristics of several tail-cone air-induction systems for air-cooled gas-turbine rotors
- The effects of fences on the high-speed longitudinal stability of a swept-wing airplane
- Comparison of the aerodynamic characteristics at transonic speeds of a plane wing and a cambered and twisted wing, both having 45 degrees of sweepback and an aspect ratio of 6
- Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound
- Effect of leading-edge chord-extensions on the aerodynamic characteristics of a 45 degree sweptback wing-fuselage combination at Mach numbers of 0.40 to 1.03
- Effect of leading-edge chord-extensions on subsonic and transonic aerodynamic characteristics of three models having 45 degrees sweptback wings of aspect ratio 4
- Effects of slot location and geometry on the flow in a square tunnel at transonic Mach numbers
- Effects of slot size and geometry on the flow in rectangular tunnels at Mach numbers up to 1.4