RT Journal Article ID 0b061f6a6f82c892 A1 Struminskaya, Irina Vladimirovna A1 Skuratov, Arkadii Sergeyevich A1 Borovoy, Volf Ya. A1 Egorov, Ivan Vladimirovich T1 PECULIARITIES OF FLOWAND HEAT TRANSFER IN THE BASE AREA OF INTERPLANETARY PROBES JF TsAGI Science Journal JO TSAGI YR 2010 FD 2011-01-26 VO 41 IS 3 SP 227 OP 257 K1 interplanetary probe K1 wind tunnel K1 numerical simulation K1 heat flux K1 Stanton number K1 separated flow K1 base flow AB 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. PB Begell House LK https://www.dl.begellhouse.com/journals/58618e1439159b1f,6b06d4b644ed07e0,0b061f6a6f82c892.html