Transonic flows around an NACA0012 airfoil were simulated by directly solving the full Navier-Stokes equations without any turbulence model. The implicit LU factored scheme was used with improved accuracy. The results of unsteady computations without any turbulence model show the clear dependence of the flow on the Reynolds number, and agree qualitatively with experimental observatiogs well even at Reynolds numbers over 10. Unsteady shock-induced vortex separation was observed at all the Reynolds numbers. To check the results against experiment, the improved scheme was coupled with the Baldwin-Lomax turbulence model obtaining excellent agreement with experiment.
|Publication status||Published - 1985 Jan 1|
|Event||AlAA 23rd Aerospace Sciences Meeting, 1985 - Reno, United States|
Duration: 1985 Jan 14 → 1985 Jan 17
|Other||AlAA 23rd Aerospace Sciences Meeting, 1985|
|Period||85/1/14 → 85/1/17|
ASJC Scopus subject areas
- Aerospace Engineering