Aerodynamic Heating of a Thin Sharp-Nose Circular Cone in Supersonic Flow

The assumption of flow symmetry is made to investigate a supersonic flow $(\text{M}_{\infty} = 5)$ past a thin circular cone with a half-angle $\theta_c = 4^{\circ}$ and an isothermal surface $(T_{w0} = 0.5)$ by way of numerical integration of unsteady-state three-dimensional Navier-Stokes and Reynolds equations. The calculations are performed in a discrete range of variation of the Reynolds number $(10^4 \le \text{Re} \le 10^8)$ and angle of attack $(0 \le \alpha \le 15^{\circ})$. The effect of the determining parameters of the problem on the structure of flow field and on aerodynamic heating of the body surface subjected to flow is demonstrated.