Supersonic wind tunnel tests and numerical analyses were carried out on the boundary layer stability. Wind tunnel tests were performed on a swept wing model. Boundary layer transition locations were detected at various angles of attack and extensions of laminar flow regions by boundary layer suction were also observed. Consequently, the validity of supersonic laminar flow control was suggested. And a boundary layer stability analyses code was developed, based on the linear stability theory, and its validity was confirmed for two dimensional boundary layers. Then one of the wind tunnel test cases was analyzed, and characteristics of disturbances were clarified.
An experimental and numerical study on the compressible laminar flow control
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