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1951•Journal of Applied PhysicsRequires access

Hypersonic Flow at a Mach Number of 10

I. D. V. Faro, T. R. Small, F. Hill

Open publisher page 5 citations

Abstract

Tests designed to produce supersonic streams at ten and sixteen times the local speed of sound are described. In contrast to the usual wind tunnel apparatus, a conical nozzle is used for the expansion section, and the supply pressure is varied throughout a wide range. Some properties of the flow at high Mach numbers are discussed, and, in particular, data are given showing a systematic dependence of Mach number on stagnation pressures, a phenomenon not previously reported.

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What this paper is about

Tests designed to produce supersonic streams at ten and sixteen times the local speed of sound are described. In contrast to the usual wind tunnel apparatus, a conical nozzle is used for the expansion section, and the supply pressure is varied throughout a wide range. Some properties of the flow at high Mach numbers are discussed, and, in particular, data are given showing a systematic dependence of Mach number on stagnation pressures, a phenomenon not previously reported.

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OpenAlex reports 5 citations for this work. Citation counts describe recorded attention and do not establish research quality.

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Available abstract

Tests designed to produce supersonic streams at ten and sixteen times the local speed of sound are described. In contrast to the usual wind tunnel apparatus, a conical nozzle is used for the expansion section, and the supply pressure is varied throughout a wide range. Some properties of the flow at high Mach numbers are discussed, and, in particular, data are given showing a systematic dependence of Mach number on stagnation pressures, a phenomenon not previously reported.

Key concepts: Mach number, Hypersonic speed, Mach wave, Nozzle, Mechanics, Aerodynamics, Supersonic speed, Conical surface

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