Numerical analysis of high-speed flow over rough surfaces

1999 by the American Institute of Aeronautics and Astronautics. All rights reserved. A numerical analysis of high-speed rough-wall compressible turbulent boundary layers was performed, where the Favre averaged turbulent boundary layer equations for compressible flow were solved. The performance of three simple algebraic rough-wall turbulence roughness models, namely van Driest, Kragstad and Cebeci-Chang, was investigated. The predicted mean flow and turbulent shear stresses were compared with recent experimental data for a Mach 2.7 boundary layer over six wind tunnel models [ks+ (0, 570)]. Overall, all three models produced numerical results that were in good agreement with each other and the experimental data. As expected, the law of the wall velocity profile shift increased with increasing roughness Reynolds number, where the defect law scaling collapsed the numerical velocity profiles. The predicted kinematic turbulent stress profiles for all six cases agreed well with the experimental data, and the results in the outer region were found to be independent of the roughness Reynolds number. The present work demonstrated that the current simple turbulence models have the essential physics necessary to accurately predict supersonic turbulent flow over a rough flat plate. 1999 by the American Institute of Aeronautics and Astronautics, Inc.

Numerical analysis of high-speed flow over rough surfaces Conference Paper