Abstract: This paper is devoted to predict laminar and turbulent
heating rates around blunt re-entry spacecraft at hypersonic
conditions. Heating calculation of a hypersonic body is normally
performed during the critical part of its flight trajectory. The
procedure is of an inverse method, where a shock wave is assumed,
and the body shape that supports this shock, as well as the flowfield
between the shock and body, are calculated. For simplicity the
normal momentum equation is replaced with a second order pressure
relation; this simplification significantly reduces computation time.
The geometries specified in this research, are parabola and ellipsoids
which may have conical after bodies. An excellent agreement is
observed between the results obtained in this paper and those
calculated by others- research. Since this method is much faster than
Navier-Stokes solutions, it can be used in preliminary design,
parametric study of hypersonic vehicles.
Abstract: A numerical study on the influence of forward-facing
cavity length upon forward-facing cavity and opposing jet combined
thermal protection system (TPS) cooling efficiency under hypersonic
flow is conducted, by means of which the flow field parameters, heat
flux distribution along the outer body surface are obtained. The
numerical simulation results are validated by experiments and the
cooling effect of the combined TPS with different cavity length is
analyzed. The numerical results show that the combined configuration
dose well in cooling the nose of the hypersonic vehicle. The deeper the
cavity is, the weaker the heat flux is. The recirculation region plays a
key role for the reduction of the aerodynamic heating.