Abstract
Recently, Nhypersonic research activities around the universe have been in major focus because of the milestone developments in hypersonic reentry vehicles, orbital transfer vehicles, reusable launch vehicles and space recovery experimental modules. One of the major problems in hypersonic flight is drag and with the tremendous progress in computational powers it can be analysed. In this work, the effects of counter flow jet on reduction of drag around two blunt cone flare bodies in the hypersonic turbulent flow are investigated through a numerical study. Flow field around the blunt bodies is calculated numerically for the free stream Mach number of 6.5. Numerical solutions of Navier-Stokes equation and energy equation governing the turbulent flow of compressible fluid are obtained by adopting Finite Volume Method (FVM) through an industry standard CFD code, FLUENT 6.3.26 package. Shear Stress Transport (SST) model was used in the computation of pressure drag, skin friction drag and total drag for both the absence of jet and the presence of jet cases for both the configuration. Contours of Mach number are presented to describe the flow patterns. It is clear that the reduction of drag was greatly influenced by the jet conditions and body shapes.
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