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- Effect of magnitude of vibratory load superimposed on mean tensile load on mechanism of and time to fracture of specimens and correlation to engine blade
- Effect of oxygen concentration of the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 turbojet combustor
- Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds
- An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades
- An analytical study of the comparative performance of four air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 1.5
- Analytical study of static and low-speed performance of thin propellers using two-speed gear ratios to obtain optimum rotational speeds
- Comparison of calculated and experimental temperatures of water-cooled turbine blades
- Combustion efficiency of homogeneous fuel-air mixtures in a 5-inch ram-jet-type combustor
- Analysis of stage matching and off-design performance of multistage axial-flow compressors
- The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources
- Aerodynamic characteristics of two-plane, unswept tapered wings of aspect ratio 3 and 3-percent thickness from tests on a transonic bump
- Characteristics of flap-type spoiler ailerons at various locations on a 60 degree delta wing with a double slotted flap
- Characteristics of swept wings at high speeds
- Combustion efficiency performance of a MIL-F-5624 type fuel and monomethylnapthalene in a single vaporizing combustor
- Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers
- Analysis of coolant-flow requirements for an improved, internal-strut-supported, air-cooled turbine-rotor blade
- An analysis of axial- and centrifugal-flow turbojet-engine performance with variable-area exhaust nozzle
- Analysis of a Nuclear-Powered Liquid-Metal Ducted-Fan Cycle
- Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear-powered aircraft
- Bodies of Revolution for Minimum Drag at High Supersonic Airspeeds
- Effect of trailing edge thickness on lift at supersonic velocities
- Effect of water vapor on combustion of magnesium hydrocarbon slurry fuels in small-scale afterburner
- The effect of various aerodynamic balances on the low-speed lateral-control and hinge-moment characteristics of a 0.20-chord partial-span outboard aileron on a wing with leading edge swept back 51.3 degrees
- The effective downwash characteristics at transonic speeds of a 6-percent-thick wing with 47 degrees of sweepback in combination with a cylindrical body as determined from force measurements of a horizontal tail
- Effects of internal configuration on afterburner shell temperatures
- Effect of fuel properties on carbon deposition in atomizing and prevaporizing turbojet combustors
- The effects of tip-mounted jet nacelles on the transonic characteristics of low-aspect-ratio wings
- Effects of three types of blunt trailing edges on the aerodynamic characteristics of a plane tapered wing of aspect ratio 3.1, with a 3-percent- thick biconvex section
- The effects of sweepback on longitudinal characteristics of a 1/30-scale semispan model of the Bell X-5 airplane as determined from NACA wing-flow tests at transonic speeds
- Effects of twist and camber, fences, and horizontal-tail height on the low-speed longitudinal stability characteristics of a wing-fuselage combination with a 45 degree sweptback wing of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6)
- Experimental and theoretical study of factors influencing the longitudinal stability of an air-to-air missile at a Mach number of 1.4
- Experimental investigation of boundary-layer suction through slots to obtain extensive laminar boundary layers on a 15-percent-thick airfoil section at high Reynolds numbers
- An experimental cascade study of the effects of a solidity reduction on the two-dimensional aerodynamic characteristics of a turbine-rotor blade suitable for air cooling
- Experimental investigation of flow in an annular cascade of turbine nozzle blades of constant discharge angle
- Experimental investigation of the effect of forebody bluntness on the pressure recovery and drag of a twin-scoop inlet-body combination at Mach numbers of 1.4 and 1.7
- An experimental investigation of the combustion properties of a hydrocarbon fuel and several magnesium and boron slurries
- Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 2.01 of nacelle shape and position on the aerodynamic characteristics in
- Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.
- Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing
- Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch
- Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance : transonic-bump method
- The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degrees sweptback, aspect-ratio-4 tail surface deflected about a skewed hinge axis
- Some observations of flow at the throat of a two-dimensional diffuser at a Mach number of 3.85
- Skin-friction drag and boundary-layer transition on a parabolic body of revolution (NACA RM-10)at a Mach number of 1.6 in the Langley 4-by-4 foot supersonic pressure tunnel
- A small-scale investigation of the effect of spanwise and chordwise positioning of an ogive-cylinder underwing nacelle on the high-speed aerodynamic characteristics of a 45 degree sweptback tapered-in-thickness wing of aspect ratio 6
- Some factors affecting fabrication and high-temperature strength of molybdenum disilicide
- Single-degree-of-freedom-flutter calculations for a wing in subsonic potential flow and comparison with an experiment
- Some stress rupture and creep properties of molybdenum disilicide in the range of 1600 to 2000 F
- Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3
- Survey of some preliminary investigations of supersonic diffusers at high Mach numbers