| Issue |
Volume 5, Juin 2013
Progress in Flight Physics
|
|
|---|---|---|
| Page(s) | 309 - 326 | |
| Section | Chapter Five. Shock interaction | |
| DOI | https://doi.org/10.1051/eucass/201305309 | |
| Published online | 14 June 2013 | |
Large-eddy simulation of high mach number film cooling with shock-wave interaction
Institute of Aerodynamics, RWTH Aachen University 5a Wüllnerstr., Aachen 52062, Germany
The impact of shock waves on supersonic cooling films is studied using large-eddy simulations (LES). A laminar cooling film is injected through a slot at a Mach number Mai = 1.8 into a fully turbulent boundary layer at a freestream Mach number Ma∞ = 2.44. The cooling film is disturbed by oblique shock waves at deflection angles of 5° and 8° at two downstream positions of the slot. At shock impingement close to the slot, i. e., within the potential-core region, at a flow deflection of 5° , a cooling effectiveness decrease of 33% occurs downstream of the separation bubble compared to a configuration without shock impingement. If the same shock impinges further downstream upon the boundary-layer region, the decrease is only 17%. The stronger 8 degree shock wave at the further downstream impingement position leads to a maximum decrease of 33%.
© Owned by the authors, published by EDP Sciences, 2013
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