A direct numerical simulation (DNS) approach is used to simulate boundary layers at supersonic speeds. The computational method is validated by comparison with experimental results of a Mach 0.3 turbulent boundary layer. Non-reacting supersonic turbulent boundary layer simulation parameters, such as the mean velocity, shear stress, structure parameter, and turbulent intensity, are found to be in agreement with experimental data. A Mach 4 turbulent boundary layer is simulated, which is represents a 26° wedge at a Mach number of 20 and 20 km altitude. In this case, the boundary layer temperature is high enough to induce chemical reactions. The endothermic chemical reaction that we simulate significantly reduces the temperature fluctuations in the boundary layer. The spanwise and wall-normal Reynolds stresses and the shear stress are increased. In addition, the pressure dilatation increases by an order of magnitude.
|Original language||English (US)|
|Number of pages||8|
|State||Published - 1998|
|Event||29th AIAA Fluid Dynamics Conference - Albuquerque, United States|
Duration: Jun 15 1998 → Jun 18 1998
|Other||29th AIAA Fluid Dynamics Conference|
|Period||6/15/98 → 6/18/98|
Bibliographical noteFunding Information:
We would like to acknowledge support from the Air
Force Office of Scientific Research Grant AF/F49620-98-1-0035. This work was also sponsored in part by the Army High Performance Computing Research Center under the auspices of the Department of the Army, Army Research Laboratory cooperative agree-ment number DAAH04-95-2-0003 / contract number DAAH04-95-C-0008. We would also like to thank Kr- ishnendu Sinha for providing the mean turbulent profiles for the supersonic cases.