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TsAGI Science Journal

ISSN Imprimir: 1948-2590
ISSN En Línea: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.v41.i3.10
pages 227-257

PECULIARITIES OF FLOWAND HEAT TRANSFER IN THE BASE AREA OF INTERPLANETARY PROBES

Volf Ya. Borovoy
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, Moscow Region, 140180 Russian Federation
Ivan Vladimirovich Egorov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Arkadii Sergeyevich Skuratov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Irina Vladimirovna Struminskaya
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia

SINOPSIS

A technique for numerically solving the unsteady Navier-Stokes and Reynolds equations was developed. On this basis a universal software system was created which enables investigation of various gas dynamic problems using different models of moving gas medium. Numerical simulation of flow over interplanetary probes was fulfilled. The experimental investigation of hypersonic flow over two models of interplanetary probe was carried out at free stream Mach numbers from 6 to 20, Reynolds numbers Re;D from 0.5×105 to 16×105, and angles of attack from 0 to 20°. These models differ, in general, by the shape of the back surface, simulating the payload capsule. The focus is on measurement of the heat flux distribution over the model back surface, including the vicinity of backward stagnation point, where the local heat flux achieves a maximum value at the symmetric overflow. Stagnation pressure distribution behind the model was measured and the near wake length was defined. The Reynolds number value at which laminar-turbulent transition takes place in the near wake within the range of Mach numbers M = 6−8 was defined. It was shown experimentally and numerically that at the turbulent base flow the heat flux to the back surface of the blunted body could be compared with the heat flux to the forward stagnation point.