The re-entry vehicles and bodies travelling in hypersonic medium face the problems of drag and surface heating for which Aerospikes have always served as a solution. Hence, design of Aerospikes plays a significant role and helps in advancement of aerodynamics of the space vehicle and research works. In this paper the effect of a stepped geometry of aerospike for varying mach number is presented. Geometry is modeled, meshed and solved. Results are verified with the results in literature. For the base geometry grid independency is studied by varying the number of elements. The flow simulations are performed using ANSYS FLUENT and the results are plotted. Results of the stepped geometry is also compared to the base geometry.
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