Global and Local Flow Solutions for HERMES 1.0

Kurzfassung

The critical heating phenomena of the winged reentry vehicle HERMES 1.0 are investigated with emphasis on questions which could not be fully resolved with previous work within "Technical Assistance to CNES concerning HERMES Aerothermodynamics". These concern the flow behaviour in the canopy region at wind tunnel flow conditions and the rudder heating at high-Mach-number flight conditions. The computation of the leeside of HERMES at wind tunnel flow conditions confirm previous results of ONERA. Surprisingly, rudder heating at flight conditions is substantially lower as compared to engineering estimates based on Stanton-Miller numbers and data for wind tunnel conditions. Extensive flow visualization is used to analyse the different flow behaviour found for wind tunnel and flight conditions.Finally, numerical computations for adiabatic boundary conditions with radiation support previous engineering methods for the windward side of HERMES which relate radiation equilibrium wall temperatures to Stanton numbers for isotherma.