Aeroheating optimisation of a hypersonic thermochemical non-equilibruim flow aroundlifting bodies during atmospheric reentry Application to: Blunt body, Delta wing, Cone-flare body

Abstract

The objective of this work is to numerically simulate a hermochemical nonequilibrium hypersonic flow around blunt bodies during atmospheric re-entry. The flow field around the hypersonic vehicle is governed by NS equations with chemical reaction source terms, accounting for the mass, momentum, and energy conservation laws. The Park chemical-kinetic model involves five neutral species, N2, O2, NO, N, O, of a kinetic mechanism of 17 reactions is applied. The chemically reacting gas flow was simulated first around the Lobb sphere blunted body to study the non-equilibrium effect of an intensive shock wave under re-entry conditions, we then investigated the trajectory design on a delta body representative shuttle orbiter configuration for the deferent angle of attack 0° to 40° at an altitude range of from 60.96 to 76.20 km for 4.88 to 7.32 km/sec velocities. Finally, we proposed a shape optimisation study between a delta lifting body and a cone-flare ballistic body. The results obtained present a good agreement with the scientific literature. Moreover, a lifting body reentry provides a high L/D ratio than a ballistic body re-entry which allow a landed intact on a runway.