Design of supersonic inlets by a computer program incorporating the method of characteristics
FORTRAN computer program for designing supersonic inlets by characteristic theory
Anderson, B. H.↗
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Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions
Evaluating performance of swirl can turbojet combustor at simulated supersonic inlet conditions
Butze, H. F.↗
Design and performance of flueric shock position sensor for a mixed-compression supersonic inlet
Design and performance of flueric shock position sensor for mixed compression supersonic inlets
Griffin, W. S.↗
Theoretical analysis of flow in VTOL lift fan inlets without crossflow
Theoretical analysis of axisymmetric flow in VTOL lift fan inlets without crossflow
Lieblein, S.↗
Performance characteristics from Mach 2.58 to 1.98 of an axisymmetric mixed-compression inlet system with 60-percent internal contraction
Performance test from Mach 2.58 to 1.98 of axisymmetric mixed-compression inlet system with 60 percent internal contraction
Cubbison, R. W.↗
Single stage experimental evaluation of variable geometry guide vanes and stator blading. Part 5 - Overall performance for variable camber guide vane and stator B with radial and circumferential inlet flow distortion
Inlet flow distortion effects on single stage variable geometry guide vanes and stators
Clark, C. E.↗
Characteristics study of a bicone mixed- compression inlet for Mach 1.80 to 2.50
Characteristics study of bicone mixed compression inlet for Mach 1.80 to 2.50
Anderson, B. H.↗
Steady-state interactions from Mach 1.98 to 2.58 between a turbojet engine and an axisymmetric inlet with 60-percent internal area contraction
Steady-state interactions between turbojet engine and axisymmetric inlet with induced distortions
Choby, D. A.↗
Restart and high response terminal shock control for an axisymmetric mixed-compression inlet with 60-percent internal contraction
Restart and high response terminal shock control for axisymmetric mixed-compression inlet with internal contraction
Cole, G. L.↗
Experimental data for two 1400-feet per second tip speed compressor rotors operated with inlet flow distortions
Performance data for high tip speed compressor rotor operated with radial and inlet airflow distortions
Bailey, E. E.↗
Experimental evaluation of outer case blowing or bleeding of single stage axial flow compressor. Part 5 - Performance of plain casing insert configuration with distorted inlet flow
Outer case bleeding or blowing effects on casing insert of single stage axial flow compressor with distorted inlet flow
Koch, C. C.↗
Performance and stall limits of a YTF30-P-1 turbofan engine with uniform inlet flow
Performance and stall limits of YTF30-P-1 turbofan engine with uniform compressor inlet flow
Braithwaite, W. M.↗
The vortex at an inlet of an air intake
Vortex at air intake inlet investigated by direct air flow visualization techniques
Miroshnichenko, A. YA.↗
Investigation of two-phase hydrogen flow in pump inlet line
Two phase hydrogen flow in pump inlet line
Connelly, R. E.↗
Characteristic design study of mixed- compression two-dimensional inlets with low-angle cowls for the Mach number range 2.70 to 1.80
Design effects on performance of two dimensional mixed-compression supersonic inlets with low angle cowls
Anderson, B. H.↗
Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction
Dynamic response of supersonic mixed compression inlet coupled to cold pipe or turbojet engine
Wasserbauer, J. F.↗
A numerical analysis of the use of perforated walls to control shock location and movement in an internal compression supersonic inlet
Numerical analysis of shock control by using perforated walls in internal compression supersonic inlets
Matthews, C. W.↗
Simplified Analytical Model for Use in Design of Pump-Inlet Accumulators for the Prevention of Liquid-Rocket Longitudinal Oscillation (POGO)
Analytical model for use in design of pump inlet accumulators for prevention of liquid rocket longitudal oscillation
Lewis, William↗