Computational Flow Analysis Of Hypersonic Reentry Blunt Body Using Fluent And Gambit

In the modern years space vehicle like rockets, reentry vehicles irrespective their unique designs needed control surfaces at hypersonic speeds. This paper explores the problem of determining the aerodynamics of cone and its effects on drag, model geometry, reentry heating, and type of flow, inlet temperature, aerodynamic heating and thermal protection systems. Taking these parameters as the motivation to find on the different body conditions at varying the Mach number the shape of this paper started after conducting enough literature survey by finding the research gap. There is no much work carried out from Numerical analysis side comparing with the Experimental work. So, to carry out the Numerical analysis initial stage from the public domain literature cone shape obtained its geometry, for accurate measurements it will then be plotted on graphs to obtain millimeter scale coordinate points. Then the geometry is created in the GAMBIT and suitable mesh element will be chosen to analyze the body external flow analysis. After successful conducting the grid independence suitable boundary conditions will be applied to run the simulation till it get converges the solution. Once the solution is converging analysis will be taking place to best suitable values expecting from Aero-mechanical features to develop the shape of the body by validating with experimental work.