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2013•TsAGI science journalRequires access

DIAGNOSTICS AND NUMERICAL SIMULATION OF FLOWS IN HYPERSONIC SHORT-DURATION WIND TUNNELS

V. Ya. Borovoy, Vladimir Nikolaevich Brazhko, Ivan Vladimirovich Egorov, Evgenii Gennadievich Zaitsev, Arkadii Sergeyevich Skuratov

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Abstract

Stagnation pressure fields and heat fluxes in two short-duration wind tunnels, UT-1M Ludwig-type shock wind tunnel (M = 6 and 8) and IT-2M hot-shot wind tunnel (M = 12 and 20) are studied experimentally and numerically. The sizes of the dynamic and thermal core flows generated by contoured and conical nozzles are determined. It is demonstrated that the flow quality in the UT-1M and IT-2M wind tunnels is sufficiently high for performing aerodynamic and thermal tests of various models. Numerical simulations of the flow in the wind tunnel nozzles and test sections ensure an adequate description of the pressure distributions and Mach number contours.

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What this paper is about

Stagnation pressure fields and heat fluxes in two short-duration wind tunnels, UT-1M Ludwig-type shock wind tunnel (M = 6 and 8) and IT-2M hot-shot wind tunnel (M = 12 and 20) are studied experimentally and numerically. The sizes of the dynamic and thermal core flows generated by contoured and conical nozzles are determined. It is demonstrated that the flow quality in the UT-1M and IT-2M wind tunnels is sufficiently high for performing aerodynamic and thermal tests of various models. Numerical simulations of the flow in the wind tunnel nozzles and test sections ensure an adequate description of the pressure distributions and Mach number contours.

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Available abstract

Stagnation pressure fields and heat fluxes in two short-duration wind tunnels, UT-1M Ludwig-type shock wind tunnel (M = 6 and 8) and IT-2M hot-shot wind tunnel (M = 12 and 20) are studied experimentally and numerically. The sizes of the dynamic and thermal core flows generated by contoured and conical nozzles are determined. It is demonstrated that the flow quality in the UT-1M and IT-2M wind tunnels is sufficiently high for performing aerodynamic and thermal tests of various models. Numerical simulations of the flow in the wind tunnel nozzles and test sections ensure an adequate description of the pressure distributions and Mach number contours.

Key concepts: Hypersonic wind tunnel, Wind tunnel, Aerodynamics, Mach number, Hypersonic speed, Supersonic wind tunnel, Nozzle, Shock (circulatory)

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