Abstract
A computational study of transonic buffet phenomenon over NACA0012 airfoil is presented using unsteady Reynolds-averaged Navier-Stokes Equations. Computations are conducted at freestream Mach numbers from 0.82 to 0.89 at zero angle of attack for Reynolds numbers of 3.0 and 10.0 million with transition fixed at 5% chord length. Numerical simulation reveals the transonic buffet occurs in a narrow range of freestream Mach numbers of 0.85-0.87. It is close to the range of freestream Mach numbers of 0.84-0.86 in which multiple solutions occur for the steady, inviscid flow. 1 The unsteady flow fields around the airfoil are examined and characterized. The shock motion frequency is found to depend on the distance between time-averaged shock wave position and trailing edge. The shock motion frequency is larger when the time-averaged shock position is closer to the trailing edge. The computational results are verified using present transonic wind tunnel experiment data. Finally the effect of a trailing edge splitter for buffet suppression is studied.
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