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- Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed IV : effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed
- Investigation of ram-jet afterburning as a means of varying effective exhaust nozzle area
- Investigation of several techniques for improving altitude starting limits of turbojet engines
- An investigation of several supersonic missile configurations directed toward minimizing center-of-pressure travel
- Measurements of pressure drop with no heat addition on mockup segments of the general electric air-cooled aircraft reactor
- Preliminary investigation at transonic speeds of the effect of balancing tabs on the hinge-moment and other aerodynamic characteristics of a full-span flap on a tapered 45 degree sweptback wing of aspect ratio 3
- Procedure for calculating turbine blade temperatures and comparison of calculated with observed values for two stationary air-cooled blades
- Comparison between prediction and experiment for all-movable wing and body combinations at supersonic speeds: Lift, pitching moment, and hinge moment
- Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets
- Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 1: two-dimensional compression-ramp inlets with semicircular cowls
- Effect of radiant energy on vaporization and combustion of liquid fuels
- Performance of an impulse-type supersonic compressor with stators
- Performance of the components of the XJ34-WE-32 turbojet engine over a range of engine and flight conditions
- Performance of pure fuels in a single J33 combustor I : five liquid hydrocarbon fuels
- Over-all performance of the J71 three-stage turbine
- Performance of air inlets at transonic and low supersonic speeds
- Oxidation-resistance mechanism and other properties of molybdenum disilicide
- Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics
- Normal accelerations and associated operating conditions on four types of commercial transport airplanes from VGH data available as of September 1951
- Investigation of afterburner performance and afterburner fuel system coking of the Westinghouse XJ34-WE-32 engine
- Preliminary investigation of a chemical starting technique for the acid - gasoline rocket propellant system
- Preliminary investigation of corrosion by molten sodium hydroxide flowing in tubes of AISI 347 stainless steel, Inconel, and nickel having average outer-wall temperatures of 1500 F and a circumferential temperature gradient of 20 F
- Preliminary free-flight investigation of the zero-lift drag penalties of several missile nose shapes for infrared seeking devices
- Preliminary investigation of a rectangular supersonic scoop inlet with swept sides designed for low drag at a Mach number of 2.7
- Preliminary free-flight investigation of the effects of rivets and lap joints on the drag of bodies at zero lift at supersonic Mach numbers to 2.1
- A preliminary gust-tunnel investigation of leading-edge separation on swept wings
- Preliminary experiments on the elastic compressive buckling of plates with integral waffle-like stiffening
- Pressure distribution at low speed on a model incorporating a W wing with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section
- Preparation and physical properties of metal slurry fuels
- Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method
- Lateral and directional dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements
- Loitering and range performance of turbojet-powered aircraft determined by off-design engine cycle analysis
- The longitudinal characteristics at Mach numbers up to 0.92 of a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10
- The longitudinal characteristics at Mach numbers up to 0.9 of a wing-fuselage-tail combination having a wing with 40 degrees of sweepback and an aspect ratio of 10
- Low-speed aerodynamic characteristics of a large-scale 45 degree swept-back wing with partial-span slats, double-slotted flaps, and ailerons
- Low-speed investigation of the effects of wing leading-edge modifications and several outboard fin arrangements on the static stability characteristics of a large-scale triangular wing
- Ignition delay experiments with small-scale rocket engine at simulated altitude conditions using various fuels with nitric acid oxidants / Dezso J. Ladanyi
- Free-spinning-tunnel investigation of a 1/30-scale model of the Grumman XS2F-1 airplane: TED No. NACA DE 366
- Friction and surface damage of several corrosion-resistant materials
- Effect of design changes and operating conditions on combustion and operational performance of a 28-inch diameter Ram-jet engine / T. B. Shillito and Shigeo Nakanishi
- Free-flight tests at Mach numbers from 0.8 to 1.4 to determine the effect on zero-lift drag of increasing the leading-edge bluntness of a 45 degree sweptback wing having an NACA 65A009 airfoil
- Measurements of thermal distortion of the submarine intermediate reactor "Mark A" moderator tube
- Effect of current design trends on airplane spins and recoveries
- Effect of fuel density and heating value on ram-jet airplane range
- Correlation of buffet boundaries predicted from wind-tunnel tests with those measured during flight tests on the F8F-1 and X-1 airplanes -transonic-bump method
- A Correlation by Means of the Transonic Similarity Rules of the Experimentally Determined Characteristics of 22 Rectangular Wings of Symmetrical Profile
- Correlation of predicted and experimental lateral oscillation characteristics for several airplanes
- Design and test of mixed-flow impellers 2: experimental results, impeller model MFI-1A
- Design and test of mixed-flow impellers 1: aerodynamic design procedure
- Design of apparatus for determining heat transfer and frictional pressure drop of nitric acid flowing through a heated tube