The flowfield of overexpanded and under expanded supersonic jets on an axisymmetric and double-wedge jet deflector has been numerically studied by solving axisymmetric and three-dimensional compressible Euler equations using a finite volume method in conjunction with three-stage Runge-Kutta time-marching scheme. The numerical simulation is carried out for the nozzle exit Mach number 2.2 and 3.1 ambient to exit pressure ratio of 1.2, 1.0, 0.8 and 0.6 and distance between nozzle exit to deflector apex ratio of 2, 3, 4 and 5 time the nozzle exit diameter. The impinging jets is characterized defined by many flow discontinuities, such as cone shock, Mach disk, reflected shock and jet boundaries. The numerical simulations consist of pressure and Mach contour and surface pressure distributions. Influence of nozzle operating pressure ratio and nozzle exit plane to deflector surface have been investigated using computational fluid dynamics CFD analysis. Flowfield produced due to impingement of cold air jet on a jet deflector has been studied using CFD and computed static pressure distribution along the deflector surface. The numerical results are compared with the available experimental data and shows good agreement between them. The numerical scheme will be useful for the design of jet deflector during the lift-off phase of a satellite launch vehicle.
R. C. Mehta (Mon,) studied this question.
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