Amit Kumar Singh
Aero Combustion Modeling Division, Aerodynamic Design and Synthesis Group, Vikram Sarabhai Space Centre, Thiruvanthapuram, India
Ankur Nagpal
Aero Combustion Modelling Division, VSSC, ISRO, Thiruvanthapuram-695022, India
G Vidya
Aerodynamics R & D Division, Aerodynamics and
Aerothermal Group, Vikram Sarabhai Space Centre
Thiruvanthapuram, India
M.M. Patil
Aeronautics entity, Vikram Sarabhai Space Centre, ISRO, Thiruvanthapuram, India
V. Ashok
Aeronautics entity, Vikram Sarabhai Space Centre, ISRO, Thiruvanthapuram, India
In this paper numerical analysis has been done at re-entry
condition of Space Shuttle STS-2 flight during descent phase of
the vehicle using CFD++ laminar solver. 7 species with 6 reactions step chemical kinetic model is used for CFD
simulation. The reaction rate constants are from Park-87 model.
Flow field details and laminar surface heat flux are computed
for the windward symmetry plane of the Space Shuttle. Results
are computed for both Equilibrium and Non-equilibrium flows
and compared with the flight heat flux data derived from
measured surface temperature. Non-equilibrium computations
are done with non-catalytic and fully catalytic wall boundary
conditions. In the present study heat flux is calculated over the windward centerline surface at M=23.4, α=39.4° and at an altitude of 71.3km. The overall result shows a good agreement with the flight data and is observed that for x/l<0.2 there exist a finite surface catalyticity and heating rates are close to non catalytic wall condition and beyond x/l>0.2, predictions from Equilibrium, Non-Equilibrium fully catalytic wall and noncatalytic wall converge and flight heating rates are close to fully catalytic wall condition.