Computational Analysis of High Speed Flow Over a Conical Surface with Changing the Angle of Attack

The work to be presented herein is a numerical analysis of flow over a 20-degree half angle cone for compressible fluid, with Mach number of 2.5 with respect to different values of angle of attacks. The problem to be solved involves formation of shock waves so that the general characteristics of supersonic flow are explored through this problem. Shock waves and slip surfaces are discontinuities in fluid mechanics problems. It is essential to evaluate the ability of numerical technique that can solve problems in which shocks and contact surfaces occur. In particular it is necessary to understand the details of developing a mesh that will allow resolution of these discontinuitiesThe results of contour plots of pressure, temperature, density and Mach number with respect of angle of attack will show that CFD is capable of predicting accurate results and is also able to capture the discontinuities in the flow, e.g., the oblique shock waves. The global comparison between the numerical and the analytical values show a good agreement.