Numerical investigation of separated transonic turbulent flows with a multipletimescale turbulence model
Abstract
A numerical investigation of transonic turbulent flows separated by curvature and shock wave  boundary layer interaction is presented. The free stream Mach numbers considered are 0.4, 0.5, 0.6, 0.7, 0.8, 0.825, 0.85, 0.875, 0.90, and 0.925. In the numerical method, the conservation of mass equation is replaced by a pressure correction equation for compressible flows and thus incremental pressure is solved for instead of density. The turbulence is described by a multipletimescale turbulence model supplemented with a nearwall turbulence model. The present numerical results show that there exists a reversed flow region at all free stream Mach numbers considered whereas various kepsilon turbulence models fail to predict such a reversed flow region at low free stream Mach numbers. The numerical results also show that the size of the reversed flow region grows extensively due to the shock wave  turbulent boundary layer interaction as the free stream Mach number is increased. These numerical results show that the turbulence model can resolve the turbulence field subjected to extra strains caused by the curvature and the shock wave  turbulent boundary layer interaction and that the numerical method yields a significantly accurate solution for the complex compressible turbulent flow.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 January 1990
 Bibcode:
 1990STIN...9021962K
 Keywords:

 Compressible Flow;
 Separated Flow;
 Shock Wave Interaction;
 Transonic Flow;
 Turbulence Models;
 Turbulent Boundary Layer;
 Turbulent Flow;
 Computational Fluid Dynamics;
 Conservation Laws;
 Continuity Equation;
 Curvature;
 Free Flow;
 KEpsilon Turbulence Model;
 Mach Number;
 Reversed Flow;
 Fluid Mechanics and Heat Transfer