TY - GEN
T1 - High-order methods for hypersonic shock wave turbulent boundary layer interaction
AU - Kokkinakis, Ioannis W.
AU - Antoniadis, Antonios F.
AU - Drikakis, Dimitris
AU - Tsoutsanis, Panagiotis
AU - Rana, Zeeshan A.
PY - 2015/1/1
Y1 - 2015/1/1
N2 - An investigation of the accuracy of high-order methods for hypersonic shock wave turbulent boundary layer interaction (SWTBLI) is presented. The numerical methods considered here comprise of the Monotone-Upstream Central Scheme for Conservation Laws (MUSCL) and Weighted Essentially Non-Oscillatory (WENO) schemes, 2nd to 9th order accurate in conjunction with structured and mixed element unstructured grids. Both Implicit Large Eddy Simulation (ILES) and Reynolds Averaged Navier-Stokes (RANS) computations have been performed. The effects of discretization on the turbulence transport equation, including the approximation method for the viscous gradient, are also investigated. The accuracy of the schemes in high Reynolds number RANS modeling is assessed against experimental data of a shock impingement on a flat plate at Mach number 5 and unit Reynolds number 37×106/m. ILES has been performed for the compression ramp case at moderate Reynolds numbers of 38.7×103, based on the boundary layer thickness, and compared to Direct Numerical Simulations (DNS).
AB - An investigation of the accuracy of high-order methods for hypersonic shock wave turbulent boundary layer interaction (SWTBLI) is presented. The numerical methods considered here comprise of the Monotone-Upstream Central Scheme for Conservation Laws (MUSCL) and Weighted Essentially Non-Oscillatory (WENO) schemes, 2nd to 9th order accurate in conjunction with structured and mixed element unstructured grids. Both Implicit Large Eddy Simulation (ILES) and Reynolds Averaged Navier-Stokes (RANS) computations have been performed. The effects of discretization on the turbulence transport equation, including the approximation method for the viscous gradient, are also investigated. The accuracy of the schemes in high Reynolds number RANS modeling is assessed against experimental data of a shock impingement on a flat plate at Mach number 5 and unit Reynolds number 37×106/m. ILES has been performed for the compression ramp case at moderate Reynolds numbers of 38.7×103, based on the boundary layer thickness, and compared to Direct Numerical Simulations (DNS).
UR - http://www.scopus.com/inward/record.url?scp=84947999111&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84947999111
SN - 9781624103209
T3 - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
BT - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
PB - AIAA American Institute of Aeronautics and Astronautics
T2 - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
Y2 - 6 July 2015 through 9 July 2015
ER -