TY - JOUR
T1 - Upstream disturbed boundary layer on compressible convex-corner flows
AU - Chung, Kung Ming
PY - 2009
Y1 - 2009
N2 - An experimental program was conducted to investigate the upstream disturbance, which in terms of upstream blowing jet, on compressible convex corner flows. The effects of blowing rate and air injection pattern were addressed. It is found that the upstream disturbance tends to decrease the local Mach number, which results in the delay in transition of subsonic and transonic expansion flows. Upstream movement of shock wave in transonic interactions is also observed, and peak pressure fluctuations are attributed to shock oscillation. The effect of air injection pattern is more pronounced on the pressure fluctuations near the convex corner.
AB - An experimental program was conducted to investigate the upstream disturbance, which in terms of upstream blowing jet, on compressible convex corner flows. The effects of blowing rate and air injection pattern were addressed. It is found that the upstream disturbance tends to decrease the local Mach number, which results in the delay in transition of subsonic and transonic expansion flows. Upstream movement of shock wave in transonic interactions is also observed, and peak pressure fluctuations are attributed to shock oscillation. The effect of air injection pattern is more pronounced on the pressure fluctuations near the convex corner.
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M3 - Article
AN - SCOPUS:70749083097
SN - 1990-7729
VL - 41
SP - 1
EP - 9
JO - Hangkong Taikong ji Minhang Xuekan/Journal of Aeronautics, Astronautics and Aviation, Series B
JF - Hangkong Taikong ji Minhang Xuekan/Journal of Aeronautics, Astronautics and Aviation, Series B
IS - 1
ER -