SEARCH · Engineering Papers
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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Effects of turbojet engine unstart on engine operation and characteristics of stall propagation through compressor and inlet system
Effect of various diffuser designs on performance of experimental turbojet combustor insensitive to radial distortion of inlet airflow
Auxiliary inlet ejector nozzle designed for supersonic cruise aircraft
Effects of engine inlet disturbances on engine stall performance
Inlet plenum chamber noise measurement comparison of 20 inch diameter fan rotors with aspect ratios of 3.6 and 6.6
Supersonic inlet engine control using engine speed as primary variable for controlling normal shock position
Inlet leak analysis for spacecraft mass spectrometer atmospheric sensor system
Wind tunnel tests for instantaneous and dynamic analysis of effects of time-variant distortions produced in supersonic inlet on J85-GE-13 turbojet engine
Wind tunnel tests to determine Mach 2.5 performance of bicone inlet with internal focused compression and 40-percent internal contraction
Experimental investigation of large scale, two dimensional, mixed compression inlet system
Wind tunnel tests of supersonic propulsion inlet, engine and exhaust nozzles
Normal shock control systems for supersonic mixed compression inlet using feedback loops
Velocity profile control tests of diffuser wall bleed to control combustor inlet airflow distribution
Starting phenomena of two-dimensional hypersonic inlets with turbulent intake boundary layers at free stream Mach 6
Inlet noise suppressors having perforated plate over honeycomb wall construction evaluated over range of passage heights and engine speeds using turbojet engine as noise source
Inlet nozzle geometry effects on subsonic flow characteristics of miniature total pressure tubes including pitot tube static and dynamic pressure and flow velocity measurements
Preliminary sector tests at 920 K of three afterburner concepts proposed for inlet temperature of 1260 F and comparison of results with conventional V-gutter flame holder