The shock wave boundary layer interaction on the suction side of transonic compressor blade is one of the main objectives of TFAST project(Transition Location Effect on Shock Wave Boundary Layer Interaction).In order ...
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The shock wave boundary layer interaction on the suction side of transonic compressor blade is one of the main objectives of TFAST project(Transition Location Effect on Shock Wave Boundary Layer Interaction).In order to investigate the flow structure on the suction side of a profile,a design of a generic test section in linear transonic wind tunnel was *** experimental and numerical results for the flow structure investigations are shown for the flow conditions as the existing ones on the suction side of the compressor *** the sidewalls the suction slots are applied for the corner flow structure *** allows to control the Axial Velocity Density Ratio(AVDR),important parameter for compressor cascade *** results for Explicit Algebraic Reynolds Stress Model with transition modeling are compared with oil flow visualization,schlieren and Pressure Sensitive *** layer transition location is detected by Temperature Sensitive Paint.
The shock wave boundary layer interaction on the suction side of transonic compressor blade is one of the main objectives of TFAST project(Transition Location Effect on Shock Wave Boundary Layer Interaction). The expe...
详细信息
The shock wave boundary layer interaction on the suction side of transonic compressor blade is one of the main objectives of TFAST project(Transition Location Effect on Shock Wave Boundary Layer Interaction). The experimental and numerical results for the flow structure investigations are shown for the flow conditions as the existing ones on the suction side of the compressor profile. The two cases are investigated: without and with boundary layer tripping device. In the first case, boundary layer is laminar up to the shock wave, while in the second case the boundary layer is tripped by the step. Numerical results carried out by means of Fine/Turbo Numeca with Explicit Algebraic Reynolds Stress Model including transition modeling are compared with schlieren, Temperature Sensitive Paint and wake measurements. Boundary layer transition location is detected by Temperature Sensitive Paint.
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