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- A study of the zero-lift drag-rise characteristics of wing-body combinations near the speed of sound
- A study of the flow over a 45 degree sweptback wing-fuselage combination at transonic Mach numbers
- Some effects of changing solidity by varying the number of blades on performance of an axial flow compressor stage
- Some effects of body cross-sectional shape, including sunken-canopy design, on drag as shown by rocket-powered-model tests at Mach numbers from 0.8 to 1.5
- Transonic flow past a wedge profile with detached bow wave
- Thrust augmentation of a turbojet engine by the introduction of liquid ammonia into the compressor inlet
- Transonic free-flight drag results of full-scale models of 16-inch-diameter ram-jet engines
- Analytical and experimental investigation of inlet-engine matching for turbojet-powered aircraft at Mach numbers up to 2.0
- Wind-tunnel investigation of a ram-jet canard missile model having a wing and canard surfaces of delta plan form with 70 degree swept leading edges : longitudinal and lateral stability and control characteristics at a Mach number of 1.60
- An analysis of the potentialities of a two-stage counterrotating supersonic compressor
- Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combination at high subsonic speeds : sweep series
- A wind-tunnel investigation of the stability of the antisubmarine rocket MK 1 Mod 0
- Effects of propeller-spinner juncture on the pressure-recovery characteristics of an NACA 1-series D-type cowl in combination with a four-blade single-rotation propeller at Mach numbers up to 0.83 and at an angle of attack of 0 degrees
- Experimental investigation of a conservatively designed turbine at four rotor-blade solidities
- Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85
- Force characteristics in the submerged and planing condition of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane
- Preliminary investigation of the drag characteristics of the NACA RM-10 missile at Mach numbers of 1.40 and 1.59 in the Langley 4- by 4-foot tunnel
- Effects of sweepback and taper on the force and cavitation characteristics of aspect-ratio-4 hydrofoils
- Performance characteristics of one convergent and three convergent-divergent nozzles
- 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 static lateral stability characteristics at M = 2.01
- Cold-air investigation of a turbine with nontwisted rotor blades suitable for air cooling
- The effects of Reynolds number at Mach numbers up to 0.94 on the loading on a 35 degree swept-back wing having NACA 65(1)A012 streamwise sections
- A correlation with flight tests of results obtained from the measurement of wing pressure distributions on a 1/4-scale model of the X-1 airplane (10-percent-thick wing)
- Evaluation of operating characteristics of a supersonic free-jet facility for full-scale ram-jet investigations
- Experimental investigation of the vibration characteristics of four designs of turbine blades and of the effect produced by varying the axial spacing between nozzle blades and turbine blades.
- Application of supersonic vortex-flow theory to the design of supersonic impulse compressor- or turbine-blade sections
- Drag of circular cylinders for a wide range of Reynolds numbers and Mach numbers
- Investigation at Mach number 1.91 of spreading characteristics of jet expanding from choked nozzles
- Investigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 3.67
- Investigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 7.4
- The effects of suction through porous leading-edge surfaces on the aerodynamic characteristics of a 47.5 degree sweptback wing-fuselage combination at a Reynolds number of 4.4 x 10(exp 6)
- Low-speed investigation of the effects of nacelles on the longitudinal aerodynamic characteristics of a 60 degree sweptback delta-wing - fuselage combination with NACA 65A003 airfoil sections
- Experimental investigation of the drag of 30 degree, 60 degree, and 90 degree cone cylinders at Mach numbers between 1.5 and 8.2
- Preliminary investigation of effect of angle of attack on pressure recovery and stability characteristics for a vertical-wedge-nose inlet at Mach number of 1.90
- Temperature response of turbine-blade metal covered with oxide coatings supplied by fuel additives
- Performance characteristics of several types of axially symmetric nose inlets at Mach number 3.85
- Some factors affecting automatic control of airplanes
- Reflection of shock waves from slotted walls at Mach number 1.62
- Investigation of liquid fluorine and hydrazine-ammonia mixture in 100-pound-thrust rocket engine
- Analytical procedures for rapid selection of coolant passage configurations for air-cooled turbine rotor blades and for evaluation of heat-transfer, strength, and pressure-loss characteristics
- The effect of bluntness on the drag of spherical-tipped truncated cones of fineness ratio 3 at Mach numbers 1.2 to 7.4
- Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls
- Relations between fuel properties and combustion carbon deposition
- Investigation of effects of additives on storage properties of fuming nitric acids
- Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : an investigation at large Reynolds numbers of the low-speed characteristics of several wing-body combinations
- Effects on the weight-flow range and efficiency of a typical axial-flow compressor inlet stage that result from the use of a decreased blade camber or decreased guide-vane turning
- Pressure drop in coolant passages of two air-cooled turbine-blade configurations
- Transonic free-flight investigation of the total drag and of the component drags (cowl pressure, additive, base, friction, and internal) encountered by a 16-inch-diameter ram-jet engine for Mach numbers from 0.80 to 1.43
- Performance of supersonic scoop inlets
- Investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections designed to have high maximum lift coefficients at low speeds