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- A preliminary evaluation of the use of ground radar for the avoidance of turbulent clouds
- Analysis of planing data for use in predicting hydrodynamic impact loads
- A rapid compression machine suitable for studying short ignition delays
- Effect of Simulated Service Conditions on Plastics During Accelerated and 2-Year Weathering Tests
- High-speed aerodynamic characteristics of horn and overhang balances on a full-scale elevator
- Investigation to determine contraction ratio for supersonic-compressor rotor
- Investigation of spark gaps subjected to altitude and air velocity conditions
- Preliminary study of use of nonstrategic metals for and application of cooling to blades of turbine of J35 turbojet engine
- Some preliminary results in the determination of aerodynamic derivatives of control surfaces in the transonic speed range by means of a flush-type electrical pressure cell
- Preliminary investigation at low speeds of swept wings in yawing flow
- Preliminary estimate of performance of a turbojet engine when inlet pressure is reduced below exhaust pressure
- Longitudinal stability and control characteristics of a semispan airplane model at transonic speeds as obtained by the transonic-bump method
- Low-speed investigation of a small triangular wing of aspect ratio 2.0 I : the effect of combination with a body revolution and height above a ground plane
- Low-speed investigation of a small triangular wing of aspect ratio 2.0 II : flaps on flat-plate models
- Notes on geared tabs at supersonic speeds
- An analytical method of estimating turbine performance
- Analytical investigation of distribution of centrifugal stresses and their relation to limiting operating temperatures in gas-turbine blades
- Calculated condenser performance for a steam turbine power plant for aircraft
- The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model
- Comparison of National Bureau of Standards ceramic coatings L-7C and A-417 on turbine blades in a turbojet engine
- An analysis of a piston-type gas-generator engine
- Preliminary investigation of cone-type diffusers designed for minimum spillage at inlet
- Effect of variation in fuel pressure on combustion performance of rectangular ram jet
- Effect of wing sweep, taper, and thickness ratio on the transonic drag characteristics of wing-body combinations
- An evaluation of air-borne radar as a means of avoiding atmospheric turbulence
- A study of skin temperatures of conical bodies in supersonic flight
- Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel. 1: the effect of Reynolds number and Mach number on the aerodynamic characteristics of the wing with flap undeflected
- Effect of airfoil profile of symmetrical sections on the low-speed static-stability and yawing derivatives of 45 degrees sweptback wing models of aspect ratio 2.61
- The effects of high-lift devices on the low-speed stability of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow
- Subsonic flight investigation of rectangular ram jet over range of altitudes
- Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord
- A theoretical lateral-stability analysis of XC-120 airplane
- Performance of 24-inch supersonic axial-flow compressor in air I : performance of compressor rotor at design tip speed of 1600 feet per second
- Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine IV: performance with tail-pipe burning and water injection
- High-speed wind-tunnel tests of a 1/78-scale model of the Lockheed YP-80A airplane
- Equations for the design of two-dimensional supersonic nozzles
- Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet
- An experimental investigation at supersonic speeds of annular duct inlets situated in a region of appreciable boundary layer
- Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area I : an inlet enclosing 61.5 percent of the maximum circumference of the forebody
- Preliminary investigation of hydrazine as a rocket fuel
- A comparison of the simulated-altitude performance of two turbojet combustor types
- Control during starting of gas-turbine engines
- Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5
- A flight investigation and analysis of the lateral-oscillation characteristics of an airplane
- Theoretical analysis of the performance of a supersonic ducted rocket
- An investigation of the downwash and wake behind large-scale swept and unswept wings
- Vibration of turbine blades in a turbojet engine during operation
- Investigation of the diborane - hydrogen peroxide propellant combination
- Effect of three flame-holder configurations on subsonic flight performance of rectangular ram jet over range of altitudes
- Experimental investigation of thrust augmentation of 4000-pound-thrust centrifugal-flow-type turbojet engine by injection of water and alcohol at compressor inlets