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Investigation of a variable Mach number supersonic tunnel with nonintersecting characteristics

J. C. Evvard, DeMarquis D. Wyatt

Abstract

Report presenting a method for the design of supersonic-wind-tunnel nozzles that produce uniform flow over a continuously variable Mach number range without the use of flexible walls. Experimental results from a preliminary investigation of the tunnel are included, including calibration survey of flow, Mach number distributions, and pressure gradients are provided.

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Available abstract

Key concepts: Mach number, Supersonic wind tunnel, Wind tunnel, Supersonic speed, Nozzle, Flow (mathematics), Range (aeronautics), Hypersonic wind tunnel