Estimation of Drag on Supersonic Cone Varying Nose Radius at Different AOA

A vehicle travelling in supersonic air flow will encounter high molecular disturbance leads to high aerodynamic heating. Its geometrical design produces shock waves resulting to form drag. In decreasing such effects, our studies lead to study various geometric shape of the nose cone. In this, the geometry varies from nose cone to blunt shape. Using CFD-FLUENT, Flow simulation is performed to observe leading edge bluntness effect on improvement of less drag during supersonic speeds. Aerodynamic loads are the major factors affecting projectile configuration.