Experimental investigation of dynamic distortion in a Mach 2.50 inlet with 60 percent internal contraction and its effect on turbojet stall margin
Dynamic distortion of supersonic wind tunnel for turbojet engines
Calogeras, J. E.↗
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Rocket-model investigation of the longitudinal stability, drag, and duct performance of a 60 deg delta wing canard aircraft with twin side inlets at Mach numbers from 0.80 to 1.70
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Bond, A. C.↗
Technique for inducing controlled steady-state and dynamic inlet pressure disturbances for jet engine tests
Secondary air injection achieving momentum interchanges to induce controlled steady state dynamic pressure disturbances for jet engine tests
Biesiadny, T. J.↗
Experimental cavitation and flashing of potassium flowing adiabatically through a Venturi sized as a boiler inlet
Cavitation and flashing of potassium flowing adiabatically through Venturi
Fenn, D. B.↗
Design of disk-gap-band and modified ringsail parachutes and development of ballute apex inlet for supersonic application
Design of parachutes and ballutes for decelerating atmospheric entries at supersonic velocities
Faurote, G. L.↗
Telescoping-spike supersonic inlet for aircraft engines Patent
Telescoping-spike supersonic nozzle for turbojet or ramjet engines
Connors, J. F.↗
Racemization of amino acids in sediments from Saanich Inlet, British Columbia
Amino acid racemization as enantiomers in core sediment samples
Brown, F. S.↗
Aerodynamic characteristics of a large-scale model with a lift fan mounted in a 5 per cent thick triangular wing, including the effects of BLC on the lift fan inlet
Aerodynamic characteristics of large-scale model with lift fan mounted in 5 percent thick triangular wing
Hall, L. P.↗
Undistorted inlet flow testing. Evaluation of range and distortion tolerance for high Mach number transonic fan stages, volume 1 Task 2 stage data and performance report
Evaluation of range and distortion tolerance for high Mach number transonic fan stages - Vol. 1
Bilwakesh, K. R.↗
Undistorted inlet flow testing. Evaluation of range and distortion tolerance for high Mach number transonic fan stages, volume 2 Task 2 stage data and performance report
Evaluation of range and distortion tolerance for high Mach number transonic fan stages - Vol. 2
Bilwakesh, K. R.↗
Absorptive splitter for closely spaced supersonic engine air inlets Patent
Absorptive, nonreflecting barrier mounted between closely spaced jet engines on supersonic aircraft, for preventing shock wave interference
Kastan, H.↗
Effects of free-stream Reynolds number, engine installation, and model scale on stability characteristics of a translating- spike inlet at Mach 2.0
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Bowditch, D.↗
Full-scale, free-jet investigation of methods of improving outlet flow distribution in a side-inlet supersonic diffuser
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Farley, J. M.↗
Wind-tunnel investigation of a wing-root inlet configuration with various modifications at Mach numbers of 1.41, 1.81, and 2.01
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Robins, A. W.↗
Experimental investigation of extreme internal flow turning at the cowl lip of an axisymetric inlet at a Mach number of 2.95
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Kowalski, K. L.↗
Effect of throat bleed on the supersonic performance of a half-conical side-inlet system
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Mc Kevitt, F. X.↗
Operation of an experimental air-cooled turbojet engine at turbine-inlet temperatures from 2200 R to 2935 R
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Cochran, R. P.↗
Survey of supersonic inlets for high Mach number applications
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Allen, J. L.↗