Analysis of Performance of a Jet Engine from Characteristics of Components II : Interaction of Components as Determined from Engine Operation
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ENGINES, TURBO-PROPELLER↗
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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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Heat-transfer processes in liquid-cooled engine cylinders I : correlation of single-cylinder engine temperatures under forced-convection cooling conditions
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COOLANTS, HIGH-TEMPERATURE-ETHYLENE GLYCOL↗
Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of a four-engine heavy bomber
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VALVE SEATS, EXHAUST↗
A fortran program to calculate an engineering estimate of the thermal radiation to the base of a multi-engine space vehicle at high altitudes
Fortran program for estimating radiant heat flux in base of arbitrary shape from intersection region caused by interaction of hydrogen-oxygen engine exhaust jets
FORTRAN↗
Medium Resolution Infra-Red /MRIR/ EXPERIMENT engineering model digital electronics telemetry unit for Nimbus ''B'' Final engineering report, 1 Nov. 1965 - 1 Apr. 1966
Medium resolution infrared experiment engineering model digital electronics telemetry unit for Nimbus B
INFRARED INSTRUMENT↗
An inviscid analysis of the plume created by multiple rocket engines and a comparison with available Schlieren data. I - Calculation of multiple rocket engine exhaust plumes by the method of characteristics. II - A finite difference method.
Multiple rocket engine exhaust plumes calculated by method of characteristics and finite difference and compared with schlieren data
ROCKET EXHAUST↗
Engineering design of a pitot-static probe payload Engineering report no. 2
Engineering aspects of instrumentation and circuitry for pitot-static probe payloads for Nike-Cajun rockets
Rupert, G. F.↗
Cooled baffle development for M-1 engine using a subscale rocket engine
Film and transpiration cooled baffles for M-1 engine
Conrad, E. W.↗
Voyager capsule engine system design considerations single versus multiple engine configuration
Single versus multiple engine configurations for Voyager capsule bus propulsion
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Engineering Science in Space, Society of Engineering Science, Technical Meeting, 5th, Huntsville, Ala., October 30- November 1, 1967, Technical Papers.
Engineering science in space - Conference, Huntsville, Alabama, October-November 1967
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Quiet engine program preliminary engine design and aircraft integration
Design considerations for integration of turbofan engine with reduced noise output in jet aircraft
Mc Bride, J. F.↗
Quiet engine program detailed engine designs
Engine design constraints for optimal noise reduction of turbofan jet aircraft
Kramer, J. J.↗
Engine quieting - Engine designs
Design and development of quiet subsonic aircraft engine
Rekos, N. F.↗
Effect of dynamic variations in engine-inlet pressure on the compressor system of a twin- spool turbofan engine
Inlet pressure oscillation effects on turbofan engine compressor
Mc Aulay, J. E.↗
Institute of Electrical and Electronics Engineers, Nuclear Science and Nuclear Power Systems Engineering Symposium, San Francisco, Calif., October 29-31, 1969, Proceedings
Nuclear science and nuclear power systems engineering - IEEE Conference, San Francisco, October 1969
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Databook for human factors engineers. Volume 1 - Human engineering data
Human factors engineering data for equipment design including anthropometry, environmental conditions, and physiological and behavioral factors
Kubokawa, C.↗
The open-cycle gas-core nuclear rocket engine: Some engineering considerations
Design, development, and characteristics of open cycle, gas core nuclear rocket engine
Taylor, M. F.↗
Effect of Reynolds number and engine nacelles on the stalling characteristics of a model of a twin-engine light airplane
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.
Lockwood, V. E.↗