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TsAGI Science Journal

ISSN Print: 1948-2590
ISSN Online: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.2019030550
pages 141-153

NUMERICAL AND EXPERIMENTAL INVESTIGATIONS OF THE AIR FLOW AND HEAT TRANSFER ALONG THE ENTIRE DUCT OF A HYPERSONIC WIND TUNNEL

Sergei Mikhailovich Drozdov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Rashid Anvarovich Davletkil'deev
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Alena Sergeevna Rtishcheva
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation

ABSTRACT

The behavior of the high-enthalpy air flow structure along the entire duct of the T-117 hypersonic wind tunnel based at the Central Aerohydrodynamic Institute (TsAGI) is studied numerically and experimentally with due allowance for the heat transfer processes in the cooler and at the wind tunnel duct walls. In numerical simulations, the hypersonic wind tunnel duct is modeled by a set of axisymmetric regions: settling chamber, contoured nozzle, schematized test section, supersonic diffuser, chamber in front of the cooler, semi-permeable region of the cooler, chamber behind the cooler, and fragment of the exhaust channel. The commercial software system ANSYS FLUENT is applied in all regions to solve the axisymmetric Navier–Stokes equations for viscous and heat-conducting air with the use of the Spalart–Allmaras and shear stress transport turbulence models. The real properties of air are simulated in the approximation of equilibrium excitation of vibrational degrees of freedom of O2 and N2 molecules. A simplified Darcy model and a slit channels model are applied for the flow in the cooler region. For flow regimes at Mach numbers ≈ 7.5 and ≈ 10.5 in the test section, the results of numerical simulations of the gas-dynamic flow in the entire duct of the T-117 wind tunnel and the heat transfer processes in the cooler and at the inner walls of the wind tunnel are analyzed and compared with the experimental data.

REFERENCES

  1. Pope, A. and Goin, K.L., High-Speed Wind Tunnel Testing, New York: Wiley, 1965.

  2. Verkhovskyi, V.P. and Nosov, V.V., The flow field investigation in the axisymmetrical contoured nozzle in the range of Mach numbers M = 7-10, Uch. Zap. TsAGI, 35(3-4), pp. 46-53, 2004.


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