Numerical investigations of shock wave interaction with laminar boundary layer on compressor profile

22nd Fluid Mechanics Conference

物理学;力学

Piotrowicz, M.^1 ; Flaszyski, P.^1

Institute of Fluid-Flow Machinery, Polish Academy of Sciences, Fiszera 14, Gdask

80-231, Poland^1

关键词: Boundary layer interaction;    Explicit algebraic reynolds stress models;    Numerical investigations;    Pressure sensitive paints;    Shock wave boundary layer interactions;    Shock wave interaction;    Transonic compressor blades;    Transonic wind tunnels;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/760/1/012023/pdf
DOI  :  10.1088/1742-6596/760/1/012023

学科分类：力学，机械学

来源: IOP

【 摘 要 】

The investigation of shockwave boundary layer interaction on suction side of transonic compressor blade is one of main objectives of TFAST project (Transition Location Effect on Shock Wave Boundary Layer Interaction). In order to look more closely into the flow structure on suction side of a profile, a design of generic test section in linear transonic wind tunnel was proposed. The experimental and numerical results of flow structure on a suction side of the compressor profile investigations are presented. The numerical simulations are carried out for EARSM (Explicit Algebraic Reynolds Stress Model) turbulence model with transition model. The result are compared with oil flow visualisation, schlieren pictures, Pressure Sensitive Paint (PSP) and static pressure.