Numerical Simulation Of Shock Wave/Turbulent Boundary Layer Interaction In Laval Nozzle

In recent years, about the problem of shock wave/turbulent boundary layer interaction and boundary layer segregation, it's mainly about exterior flow field of supersonic and high supersonic aircraft.But it's very few to research interior flow field of Laval nozzle. It's very useful to research interior flow field of Laval nozzle. So, the paper researches the problem of shock wave/turbulent boundary layer interaction and boundary layer segregation.In the paper, the parameters of Laval nozzle use the sprayer of Baosteel'300t converter. The part of shrink is quintic curve, the part of expand is 0.5arc to connect the part of shrink. The medium is air, and use the semi-empirical formula to modify the boundary layer.In the facet of numerical simulation, we use the second-order-accurate FVM and the model of Spalart-Allmaras to simulate the N-S equation.First, the paper is compared the turbulent model S-A to κ-ε and κ-ω in several facets, and choose the S-A model to simulate. Second, through calculation, we found: The form of shock wave is combination shock wave, and then we analyzed the reason of it. Last, through changing the pressure of Laval nozzle's outlet, we get the relationship between pressure and the position of shock wave, between pressure and the position of segregation, and then get the curveThe results and the methods can give reference to Laval nozzle of designer.