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

Abstract

The assumption of flow symmetry is made to investigate a supersonic flow (M ∞ = 5) past a thin circular cone with a half-angle θ c = 4° 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 ≤ Re ≤ 10 8 ) and angle of attack (0° ≤ α ≤ 15°). 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.

Pressure-sensitive paint on a truncated cone in hypersonic flow at incidences

“…Significant crossflow occurs from windward side to leeward side. The surface flow pattern for a thin sharp nose cone model is reported at similar conditions by Bashkin et al 47 The crossflow is much apparent from the oil flow results.…”