A numerical method for the direct simulation of supersonic turbulent boundary layers is being developed. A weighted essentially nonoscillatory shock-capturing scheme with low dissipation has been combined with a time-accurate, implicit solution advancement technique and implemented on a massively parallel supercomputer. Temporal boundary layer simulations at Mach 2 and Mach 4 validate the numerical method for situations in which Morkovin's hypothesis holds. These test conditions are used so that the traditional methods used as baselines for comparison are reliable. The DP2 time integration scheme uses 15% of the CPU time of the Runge-Kutta method and yields essentially identical results. For the flux Jacobian implemented here, the adaptive ENO solutions are in excellent agreement with those predicted by a highorder upwind-biased spatial differencing scheme, and turbulent fluctuations are not damped significantly. Conclusions can not yet be drawn regarding the numerical scheme's performance beyond the range of Morkovin's hypothesis: the lack of reliable data for comparisons is the very motivation for the development of the numerical method. Nonetheless, the implicit essentially nonoscillatory method described is promising for direct simulations of supersonic turbulent boundary layers.
|Original language||English (US)|
|State||Published - 1998|
|Event||36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States|
Duration: Jan 12 1998 → Jan 15 1998
|Other||36th AIAA Aerospace Sciences Meeting and Exhibit, 1998|
|Period||1/12/98 → 1/15/98|
Bibliographical notePublisher Copyright:
© 1997 by V. Gregory Weirs. Published by the American Institute of Aeronautics and Astronautics, Inc.