Abstract
A supersonic flat plate boundary layer at Reynolds number of 2 × 104 based on the inflow boundary layer thickness is investigated at different Mach numbers (M=2.88 and 4) using the Monotonically Integrated Large Eddy Simulation (MILES) technique. The inherent numerical dissipation is taken as an implicit SGS model to close the Favre-filtered compressible Navier-Stokes (NS) equations. A finite volume method with the second order accuracy in time and space is implemented for the solution of the Navier-Stokes equations on an unstructured grid of tetrahedra. The heat transfer coefficient is predicted by simulating both adiabatic and isothermal cases. The mean flowfield and turbulent stresses are in good agreement with experiment. The relationship between the predicted skin friction coefficient and heat transfer coefficient is in close agreement with the Reynolds analogy factor. The variation of turbulent Prandtl number cross the boundary layer falls within the experimental envelope.
| Original language | English (US) |
|---|---|
| State | Published - 2002 |
| Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: Jan 14 2002 → Jan 17 2002 |
Other
| Other | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
|---|---|
| Country/Territory | United States |
| City | Reno, NV |
| Period | 1/14/02 → 1/17/02 |
All Science Journal Classification (ASJC) codes
- Space and Planetary Science
- Aerospace Engineering