Impact of 3D Shock Control Bumps on Transonic Buffet
Steady and unsteady RANS computations have been carried out to investigate the effect of three dimensional shock control bumps on the buffet behaviour of a transonic airfoil. A total of five basic bump shapes were investigated at two Mach numbers. All bumps were optimized for minimal drag at a single design point by varying the two parameters bump height and bump position. In total two design points were investigated. The first one was located at the higher Mach number at a angle of attack close to cruise conditions while the second design point was located at the lower Mach number close to the buffet boundary. Additionally, the applicability of separation as buffet indicator, the effect of streamwise vortices on the buffet alleviation and innovative bump shapes were examined. For a suitable test case the employed finite volume solver TAU shows a close-to-linear scaling up to high domain numbers beyond 10,000, which corresponds to less than 14,000 cells per partition. Additionally the differences achieved utilizing different compilers and partitioners are discussed.
KeywordsMach Number Lift Coefficient Streamwise Vortex Streamwise Vorticity Maximum Lift Coefficient
The research leading to these results has received funding from the European Union’s Seventh Framework Programme (FP7/2007–2013) for the Clean Sky Joint Technology Initiative under grant agreement no. 271843.
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