Hypersonic Flow Past Unyawed Circular Cones


Abstract

An approximate closed form solution to the inviscid hypersonic flow over a circular cone, at zero angle of incidence, with an attached shock wave is considered here. It has been assumed that viscosity is zero and there exists thermodynamic equilibrium. The dissociation and ionization of air are completely neglected. The importance of the solution is that the shock wave angle, velocity, density, pressure, temperature, pressure and drag co-efficient on the surface of the cone etc. have been expressed in terms of only two independent variables, namely the semi-vertical angle of the cone and the free stream mach number.

Subject Discipline

Mathematical Sciences

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