Reingestion characteristics and inlet flow distortion of V/STOL lift-engine fighter configurations
Reingestion characteristics and inlet flow distortion of V/STOL fighter powered by J-85 engine
Barrack, J. P.↗
SEARCH · Search NASA
Results for “Inlets”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Numerical study of control of dynamic properties of a supersonic inlet using bypass bleed
Numerical study on controlling dynamic properties of supersonic inlet using bypass bleed
Matthews, C. W.↗
Inlet flow distortion testing. Evaluation of range and distortion tolerance for high Mach number transonic fan stages, volume 1 Task 2 stage data and performance report
Inlet flow distortion testing of high Mach number transonic fan stages - Vol. 1
Doyle, V. L.↗
Inlet flow distortion testing. Evaluation of range and distortion tolerance for high Mach number transonic fan stages, volume 2 Task 2 stage data and performance report
Tabular data derived from inlet flow distortion tests of high Mach number transonic fan stages - Vol. 2
Doyle, V. L.↗
Study and development of turbofan nacelle modifications to minimize fan-compressor noise radiation. Volume 5 - Sonic inlet development Contractor report, 1 May 1967 - 1 Nov. 1969
Static tests to determine effects of throat inlet concepts on forward-radiated fan noise of 707-320B/C airplanes
Source record↗
Unstart and stall interactions between a turbojet engine and an axisymmetric inlet with 60-percent internal-area contraction
Effects of turbojet engine unstart on engine operation and characteristics of stall propagation through compressor and inlet system
Burstadt, P. L.↗
Effect of various diffuser designs on the performance of an experimental turbojet combustor insensitive to radial distortion of inlet airflow
Effect of various diffuser designs on performance of experimental turbojet combustor insensitive to radial distortion of inlet airflow
Biaglow, J. A.↗
Effect of exit area variation on the performance of an auxiliary inlet ejector nozzle at Mach numbers from 0 to 1.27
Auxiliary inlet ejector nozzle designed for supersonic cruise aircraft
Blaha, B. J.↗
Effects of engine inlet disturbances on engine stall performance
Effects of engine inlet disturbances on engine stall performance
Burcham, F. W., Jr.↗
Inlet plenum chamber noise measurement comparison of 20-inch diameter fan rotors with aspect ratios 3.6 and 6.6
Inlet plenum chamber noise measurement comparison of 20 inch diameter fan rotors with aspect ratios of 3.6 and 6.6
Gelder, T. F↗
A supersonic inlet-engine control using engine speed as a primary variable for controlling normal shock position
Supersonic inlet engine control using engine speed as primary variable for controlling normal shock position
Hagedorn, R. E.↗
Combined study program. Volume 4 - Inlet leak study Final report
Inlet leak analysis for spacecraft mass spectrometer atmospheric sensor system
Moore, G. V.↗
Instantaneous and dynamic analysis of supersonic inlet-engine compatibility
Wind tunnel tests for instantaneous and dynamic analysis of effects of time-variant distortions produced in supersonic inlet on J85-GE-13 turbojet engine
Burstadt, P. L.↗
Mach 2.5 performance of a bicone inlet with internal focused compression and 40 percent internal contraction
Wind tunnel tests to determine Mach 2.5 performance of bicone inlet with internal focused compression and 40-percent internal contraction
Choby, D. A.↗
Experimental investigation of a large scale, two-dimensional, mixed compression inlet system - Performance at supersonic conditions, M equals 1.55 to 3.2
Experimental investigation of large scale, two dimensional, mixed compression inlet system
Anderson, W. E.↗
Inlet-engine-nozzle wind tunnel test techniques
Wind tunnel tests of supersonic propulsion inlet, engine and exhaust nozzles
Bowditch, D. N.↗
Experimental and analytical investigation of fast normal shock position controls for a Mach 2.5 mixed-compression inlet
Normal shock control systems for supersonic mixed compression inlet using feedback loops
Cole, G. L.↗