Abstract
An experimental study was conducted to investigate the effect of Reynolds number on compressible convex-corner flows, which correspond to an upper surface of a deflected flap of an aircraft wing. The flow is naturally developed along a flat plate with two different lengths, resulting in different incoming boundary layer thicknesses or Reynolds numbers. It is found that boundary layer Reynolds number, ranging from 8.04×104 to 1.63×105, has a minor influence on flow expansion and compression near the corner apex in the transonic flow regime, but not for the subsonic expansion flow. For shock-induced separated flow, higher peak pressure fluctuations are observed at smaller Reynolds number, corresponding to the excursion phenomena and the shorter region of shock-induced boundary layer separation. An explicit correlation of separation length with deflection angle is also presented.
Original language | English |
---|---|
Pages (from-to) | 443-454 |
Number of pages | 12 |
Journal | Advances in Aircraft and Spacecraft Science |
Volume | 1 |
Issue number | 4 |
DOIs | |
Publication status | Published - 2014 Oct 1 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fluid Flow and Transfer Processes