Abstract
Unsteady supersonic turbulent gas flow over a plane cavity is simulated numerically. The solution is determined by means of the joint integration of the Reynolds equations and the two-parameter turbulence model using the law of the wall. The calculation results obtained for various cavity trailing edge contours are considered. The strong effect of the geometry of the trailing edge on the flow parameter fluctuation intensity is demonstrated. A surface shape which makes it possible considerably to reduce these oscillations is determined.
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