Flow structure of a supersonic jet impinging on an axisymmetric deflector

The flow structure of an under- and overexpanded supersonic jets impinging an an axisymmetric deflector has been numerically and experimentally investigated. The impinging jet is characterized by many discontinuities, such as jet shock, jet boundary, Mach disk, reflected shock ann cone shock, In the numerical computations, the two-stage Runge-Kutta time-stepping scheme is employed to solve compressible, axisymmetric Euler equations. The experiment consists of schlieren flow visualisation and measurements of pressure distributions. Effects of exit Mach number, expansion ratio and distance between nozzle exit plane to the apex of the deflector on flow structure of the jets are studied with the help of schlieren pictures, Mach contours and vector plots, Comparison of the present numerical analysis with the experimental results exhibit good agreement. It is observed that the vector plots of the impinging free jets differ appreciably from the impinging vector plots and formation of vortex is found in the vicinity of the deflector.