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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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Rocket exhaust research in areas of direct impingement heating, backwash base heating, radio signal attenuation, and interference with line of sight to ground stations
Impingement of condensed rocket exhaust gases upon proximate space vehicles
Pressures and heat transfer rate predictions for rocket exhaust impingement on flat plates and curved panels
Variable geometry requirements in exhaust nozzles and inlets for high Mach number applications
Computer program manual to analyze loads and heating on bodies subject to rocket exhaust impingement
Rocket exhaust plume problems including heating, structural loads, line of sight interference and radio signals attenuation
Condensed rocket exhaust products impingement on nearby spacecraft during propulsive maneuvers, noting mission profile constraints due to momentum flux and damage
IR radiation heat transfer from rocket exhaust plumes, discussing absorption and emission characteristics
Spectral radiance of rocket exhaust plumes at high altitudes
Lunar module descent engine exhaust effect on lunar surface temperatures
Model rocket exhaust plumes spectral radiance at high altitudes measured by rapid scanning IR spectrometer
Three dimensional interaction of multirocket vehicle exhaust jet plumes calculated, using finite difference analog to inviscid flow equations
Atmospheric wind profiles from ground to high altitudes measured from large rocket engine exhaust noise data
Variable geometry supersonic aircraft design, discussing inlet and exhaust nozzles problems and wind tunnel tests
Data from absorption coefficients and fine-structure parameters measured for water vapor have been incorporated in an analytic program useful in evaluating heating by radiation from the exhaust plume of a large rocket.
Prediction formula for sound generating mechanism of turbofan engine exhaust
Flow field from forward facing nozzles exhausting near large cylindrical body at free-stream Mach numbers of 3.0 and 6.0
Experimental study to locate acoustic sources in Mach 2.5 jet exhaust stream