Projects per year
High-order implicit Large Eddy Simulations were conducted to study shock-boundary layer interaction around a 33° compression corner at Mach 7.2 and Reynolds number of Reθ = 3,500 based on the momentum thickness. A grid-convergence study was performed to reduce the computational uncertainty and the results were compared with experiments and theoretical predictions. Furthermore, the turbulent flow properties were analysed with respect to the Reynolds normal stress, skewness and flatness, and conclusions were drawn regarding the shock boundary layer interaction behavior.
|Title of host publication||2018 AIAA Aerospace Sciences Meeting|
|Place of Publication||Reston, VA|
|Publication status||Published - 8 Jan 2018|
|Event||AIAA SciTech 2018 - Gaylord Palms, Kissimmee, United States|
Duration: 8 Jan 2018 → 12 Jan 2018
|Conference||AIAA SciTech 2018|
|Period||8/01/18 → 12/01/18|
- large eddy simulations
- shock-boundary layer interaction
- grid-convergence stud
- turbulent flow properties
FingerprintDive into the research topics of 'Physical insight into a Mach 7.2 compression corner flow'. Together they form a unique fingerprint.
- 1 Finished
Drikakis, D. & Kokkinakis, I.
30/09/15 → 29/09/17