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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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High lift characteristics of variable-sweep transport model with blended engine-fuselage and engine-mounted horizontal tails
Low-speed characteristics of variable-sweep supersonic transport model with blended engine fuselage and engine-mounted tails
Surveys of engineering school needs in field of biomechanical and human factors engineering education
Computer and engine performance study of jet engine generalized parameter fuel control
Thermodynamic performance test analyses for Apollo spacecraft ascent, descent, and service propulsion system engines to define hypergol engine restart limits
Cold flow and hot firing test details for Apollo spacecraft ascent, descent, and service propulsion system engines to define hypergol engine restart limits
Fluid mechanics and engine dynamics and start-up experiments simulating thermal environment in nuclear light bulb engine
Coupled supersonic inlet-engine control using overboard bypass doors and engine speed to control normal shock position
Validating gas generator method of calculating jet engine thrust, and evaluation of XB-70-1 engine performance at ground static conditions
Engineering methods for predicting temperatures and velocities in vicinity of vertical lift engines of jet V/STOL aircraft operating near ground
Effects of engine inlet disturbances on engine stall performance
Supersonic inlet engine control using engine speed as primary variable for controlling normal shock position
Turbofan engine designs and tests for engine noise reduction
Low pressure turbofan rotor, stator, frame, and exhaust nozzle designs for turbofan engine noise reduction including acoustics and engine tests
A preliminary design study of a conceptual 6000-MW open-cycle gas-core nuclear rocket engine system was made. The engine has a thrust of 44,200 lb and a specific impulse of 4400 sec. The nuclear fuel is uranium-235 and the propellant is hydrogen. Critical fuel mass was calculated for several reactor configurations. Major components of the reactor (reflector, pressure vessel) and the waste heat rejection system were considered conceptually and were sized.
This document is Volume 2 of three volumes of the Final Report for the four band Multispectral Scanner System (MSS). The results are contained of an analysis of pictures of actual outdoor scenes imaged by the engineering model MSS for spectral response, resolution, noise, and video correction. Also included are the results of engineering tests on the MSS for reflectance and saturation from clouds. Finally, two panoramic pictures of Yosemite National Park are provided.
Activities in packaging components into integral module arrangements compatible with engine design requirements for the 1137400E flight engine baseline are summarized along with the applied mechanics and thermal analysis. Revisions to drawings, configurations, and support structures are discussed.
Methods for predicting the base heating characteristics of a multiple rocket engine installation are discussed. The environmental data is applied to the design of adequate protection system for the engine components. The methods for predicting the base region thermal environment are categorized as: (1) scale model testing, (2) extrapolation of previous and related flight test results, and (3) semiempirical analytical techniques.