Numerical and experimental study of the Mach 2 pseudo-shock wave in a supersonic duct
This paper presents an investigation on the structure and characteristics of the multiple shock wave/turbulent boundary layer interaction in a Mach 2 supersonic square duct by numerical simulation and experiment. The numerical simulation is carried out with the Harten-Yee’s second-order accuracy TVD scheme and the Baldwin- Lomax’s turbulence model. The flow conditions are: free stream Mach number M∞ = 2.0, unit Reynolds number Re∞/m = 2.5xl07m−1, and the flow confinement is δ∞/h = 0.25. Good agreements between the numerical analysis and the experiment for the shape of the shock train and wall pressure distribution along the duct are obtained. Based on these agreements, the flow quantities, which are difficult to obtain by experiment, are analyzed by numerical simulation.
KeywordsMach Number Static Pressure Distribution Free Stream Mach Number Shock Train Schlieren Photograph
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