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