S. A. Glazkov  , A. R. Gorbushin  , A. V. Semenov  , A. V. Ledovsky  , G. A. Trashkov

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018-29801111

The paper is devoted to the study of the influence of wind tunnel perforated walls on the aerodynamic characteristics of the reentry vehicle model at transonic speed. An experimental investigations were carried out with model at zero angle of attack in the TsAGI transonic wind tunnel T-128 within the range of Mach number М=0.9-1.1 at various porosity values of test section walls F=2%; 6%; 10%. Aerodynamic forces and moments, acting on the model, were measured by 6- component internal strain gauge balance. A distribution of static pressure on the model surface and on test section perforated walls was measured along with static pressure fluctuations on the model. Parameters of the boundary layer on the perforated wall were measured by means of the rake with total pressure probes. Numerical investigations of the flow around the model in test section were performed by solving Reynolds Averaged Navier-Stocks (RANS) equations using Electronic Wind Tunnel software (EWT-TsAGI). Satisfactory agreement was obtained between the computational and experimental data on the influence of the test section perforated walls on the aerodynamic characteristics of the model and the flow parameters on the wall. The influence of the perforation coefficient on the model drag coefficient in the calculations and in the experiment turned out to be the same.

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In Categories: High-Speed Aerodynamics and Aerothermodynamics, HiSST 2018, Hypersonic Aerodynamics, Supersonic and Hypersonic Aircraft Design
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