DOI: https://doi.org/10.36347/sjet.2026.v14i02.003

Pages: 90-118

Comprehensive flowfield study of supersonic jets impinging over a double-wedge deflector and an inclined plate and has been carried out by solving computational fluid dynamics (CFD) method and analytical method based on oblique shock relations. Three-dimensional compressible inviscid equations are solved employing finite volume methods using a multistage Runge-Kutta time stepping scheme. The numerical simulation is carried out for Me = 2.2 and 3.1, Te = 152oK, 266oK and 1811oK, pe/pe = 1.2, 0.8 and 0.6 and Xw/De = 3, 4 and 5. The supersonic jets emanating from a convergent-divergent nozzle impinging on a jet deflector can be customarily characterized by many flow discontinuities such as reflected shock, oblique shock, Mach disc, slip line, wedge shock and wall jet boundaries. The CFD results consist of pressure, density, Mach and temperature contour and surface pressure distributions. Influence of nozzle operating pressure ratio and nozzle exit temperature on the flowfield have been investigated using CFD analysis and compared with the experimental data of hot test cases of a solid rocket motor. On the base of space vehicle induced recirculation region is observed in the CFD simulation. The main focus of the present paper is to numerically analyze cold and hot jets and to investigate the effect of ratio of specific heats on flowfield of a double-wedge deflector. The numerical results are compared with the available experimental data and exhibit agreement between them. The numerical analysis will be useful for the selection of appropriate jet deflector during the lift-off phase of a space vehicle.