AXISYMMETRIC BODY AT AN ANGLE OF ATTACK IN HYPERSONIC FLOW: HEAT PROBLEM

摘要

Hypersonic flow (M_∞ = 7.9) over a Martian probe model of the Martian Sample Return Orbiter type with an isothermal surface (in which the temperature factor is T_(w0) = 0.375) at an angle of attack (0 ≤ α ≤ 40°) is calculated based on the unsteady three-dimensional Navier-Stokes equations. The temperature field structure and the thermal characteristics in the flow symmetry plane and their evolution with the angle of attack are investigated.