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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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Fortran program for estimating radiant heat flux in base of arbitrary shape from intersection region caused by interaction of hydrogen-oxygen engine exhaust jets
Medium resolution infrared experiment engineering model digital electronics telemetry unit for Nimbus B
Multiple rocket engine exhaust plumes calculated by method of characteristics and finite difference and compared with schlieren data
Engineering aspects of instrumentation and circuitry for pitot-static probe payloads for Nike-Cajun rockets
Film and transpiration cooled baffles for M-1 engine
Single versus multiple engine configurations for Voyager capsule bus propulsion
Engineering science in space - Conference, Huntsville, Alabama, October-November 1967
Design considerations for integration of turbofan engine with reduced noise output in jet aircraft
Engine design constraints for optimal noise reduction of turbofan jet aircraft
Design and development of quiet subsonic aircraft engine
Inlet pressure oscillation effects on turbofan engine compressor
Nuclear science and nuclear power systems engineering - IEEE Conference, San Francisco, October 1969
Human factors engineering data for equipment design including anthropometry, environmental conditions, and physiological and behavioral factors
Design, development, and characteristics of open cycle, gas core nuclear rocket engine
The investigation was made on a 1/18-scale model of a twin-engine light airplane. Static longitudinal, lateral, and directional characteristics were obtained at 0 deg and plus or minus 5 deg sideslip at a Mach number of about 0.2. The angle of attack varied from about 20 deg at a Reynolds number of 0.39 times one million to 13 deg at a Reynolds number of 3.7 times one million, based on the reference chord. The effect of fixed transition, vertical and horizontal tails, and nacelle fillets was studied.
The performance testing and analytical teardown of CF6-6D engine serial number 451-380 which was recently removed from a DC-10 aircraft is summarized. The investigative test program was conducted inbound prior to normal overhaul/refurbishment. The performance testing included an inbound test, a test following cleaning of the low pressure turbine airfoils, and a final test after leading edge rework and cleaning the stage one fan blades. The analytical teardown consisted of detailed disassembly inspection measurements and airfoil surface finish checks of the as-received deteriorated hardware. Aspects discussed include the analysis of the test cell performance data, a complete analytical teardown report with a detailed description of all observed hardware distress, and an analytical assessment of the performance loss (deterioration) relating measured hardware conditions to losses in both specific fuel comsumption and exhaust gas temperature.