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- Effects of leading-edge slats on the aerodynamic characteristics of a 45 degree sweepback wing-fuselage configuration at Mach numbers of 0.4 to 1.03
- Internal performance of several types of jet-exit configurations for supersonic turbojet aircraft
- A study of the effects of body shape on the vortex wakes of inclined bodies at a Mach number of 2
- Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 1: effect of air bleed at compressor outlet
- Comparison of the experimental and theoretical distribution of lift on a slender inclined body of revolution at M = 2
- Experimental investigation of the effects of support interference on the pressure distribution of a body of revolution at a Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 14 x 10(exp 6)
- Effect of rotor- and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 2: redesigned compressor for XJ-40-WE-6 engine
- Effect of rotor-and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 1: original production compressor of XJ40-WE-6 engine
- Performance of a supersonic mixed-flow rotor with a swept leading edge and 0.52 inlet radius ratio
- Performance of a swept leading edge rotor of the supersonic type with mixed flow
- Investigation at supersonic speeds of an inlet employing conical flow separation from a probe ahead of a blunt body
- Test of an aerodynamically heated multiweb wing structure (MW-1) in a free jet at Mach number 2
- Method for estimating combustion efficiency at altitude flight conditions from combustor tests at low pressures
- Spark ignition of flowing gases III : effect of turbulence promoter on energy required to ignite a propane-air mixture
- Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds
- Investigation of translating-spike supersonic inlet as means of mass-flow control at Mach numbers of 1.5, 1.8, and 2.0
- Utilization of external-compression diffusion principle in design of shock-in-rotor supersonic compressor blading
- Thermal shock resistance and high-temperature strength of a molybdenum disilicide - aluminum oxide ceramic
- Wind-Tunnel Investigation of a 1/15-Scale Model of the Republic MX-1554 Airplane at Mach Numbers of 1.45 and 1.90
- Wind-tunnel investigation of a 45 degree sweptback wing having a symmetrical root and a highly cambered tip, including the effects of fences and lateral controls
- Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing
- Wind-tunnel investigation at subsonic and supersonic speeds of a model of a tailless fighter airplane employing a low-aspect-ratio swept-back wing : effects of external fuel tanks and rocket packets on the drag characteristics
- Wind-Tunnel Investigation of a Modified 1/20-Scale Model of the Convair MX-1554 Airplane at Mach Numbers of 1.41 and 2.01
- Matched performance characteristics of a 16-stage axial-flow compressor and a 3-stage turbine
- Lift, drag, and hinge moments at supersonic speeds of an all-movable triangular wing and body combination
- Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : comparison of three wings of aspect ratio 2 of rectangular, swept-back and triangular plan form, including effects of thickness distribution
- Mechanical design analysis of several noncritical air-cooled turbine disks and a corrugated-insert air-cooled turbine rotor blade
- Preliminary drag and heat-transfer data obtained from air-launched cone-cylinder test vehicle over Mach number range from 1.5 to 5.18
- Magnesium-slurry combustion performance in 6.5-inch-diameter ram-jet engine mounted in connected-pipe facility
- Performance of a turbojet engine with adjustable first-stage turbine stator and variable-area exhaust nozzle
- Photographic investigation of combustion in a two-dimensional transparent rocket engine
- Investigation at Mach numbers 1.5 and 1.7 of twin-duct side intake system with two-dimensional 6 degree compression ramps mounted on a supersonic airplane
- Effects of additives on pressure limits of flame propagation of propane-air mixtures
- Investigation of distribution of losses in a conservatively designed turbine
- Effect of diffuser design, diffuser-exit velocity profile and fuel distribution on altitude performance of several afterburner configurations
- An extension of the investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61
- Diffusion factor for estimating losses and limiting blade loadings in axial-flow-compressor blade elements
- A theoretical analysis of the distortion of fuel-spray-particle paths in a helicopter ram-jet engine due to centrifugal effects
- Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10
- An experimental investigation of the transonic-flow-generation and shock-wave-reflection characteristics of a two-dimensional wind tunnel with 24-percent-open, deep, multislotted walls
- Comparison of theoretically and experimentally determined effects of oxide coatings supplied by fuel additives on uncooled turbine-blade temperature during transient turbojet-engine operation
- Applications of auxiliary air injectors to supersonic wind tunnels
- Investigations of the damping in roll of swept and tapered wings at supersonic speeds
- Effect of vertical position of the wing on the aerodynamic characteristics of three wing-body combinations
- Experimental and theoretical investigation of rotating-stall characteristics of single-stage axial-flow compressor with hub-tip ratio of 0.76
- Theoretical performance of mixtures of liquid ammonia and hydrazine as fuel with liquid fluorine as oxidant for rocket engines
- Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant
- The influence of vortex generators on the performance of a short 1.9:1 straight-wall annular diffuser with a whirling inlet flow
- Performance Characteristics of a 24 Degree Straight-Outer-Wall Annular-Diffuser-Tailpipe Combination Utilizing Rectangular Vortex Generators for Flow Control
- Effects of wing elasticity on the aerodynamic characteristics of an airplane configuration having 45 degrees sweptback wings as obtained from free-flight rocket-model tests at transonic speeds