The vehicle moving at hypersonic speed experience forces which leads to slow-down of the vehicle. This flow of fluid which makes it slow is known as drag which plays important role while designing hypersonic rockets for mars mission. Air drag is also plays an important role in the designing of the vehicle. The objective of the aerospace industry is to develop the nose cone that can travel at high speed by producing optimum value of air drag & force. This investigation deals with computational analysis of the spherical blunted tangent ogive nose cone profile of rocket at hypersonic velocity. The outcome of nose-cone design on the drag is studied at hypersonic flow. The paper aim is recognize specific aerodynamic characteristics with minimum drag at particular Mach number with considering density, temperature, viscosity, pressure, velocities for the hypersonic flight. The area of this paper is to develop some profile with outstanding aerodynamic qualities and low cost for use in construction projects for hypersonic mission by improving their efficiency and effect on target. The present problem is analysed in ANSYS fluent software. Flow over a body is observed in numerical simulation for particular Mach number for spherical blunted tangent ogive nose cone profile & the parameters such as critical design aspects and performance characteristics of the selected nose cone are presented.

Keywords : Mach Number, Hypersonic Flows, Nose Profiles, Aerodynamic, ANSYS Fluid Fluent.