The present study deals with solving two-dimensional Reynolds Averaged Navier-Stokes equations for the Fire II re-entry capsule using Computational Fluid Dynamics (CFD). The primary goal is to model the aero thermodynamic flow characteristics around the capsule and estimate the surface heat flux distribution. Mach number value of 15.16 is chosen as a free stream condition corresponding to an altitude of 50 km. Taking advantage of the symmetry, only a quarter portion of the geometry is considered to generate the volume mesh for the simulation. The numerical models and convergence techniques that are implemented by the CFD solver are thoroughly described.
Special attention has been paid to validate the code. The value of shock stand-off distance obtained by means of benchmark empirical formulation is compared to the CFD analysis. An additional comparison between the simulated results and the approximated engineering correlations of convective stagnation point heat fluxes is made to ensure the validity of the obtained results. Overall, a satisfactory agreement is observed between the estimated values by engineering correlations and those predicted by the numerical solver.
|Commitee:||Chen, Hsin-Piao, Lewis, James|
|School:||California State University, Long Beach|
|Department:||Mechanical and Aerospace Engineering|
|School Location:||United States -- California|
|Source:||MAI 57/06M(E), Masters Abstracts International|
|Subjects:||Fluid mechanics, Aerospace engineering|
|Keywords:||Aero-thermodynamics, Computational fluid dynamics, High speed aerodynamics, Re-entry vehicles, Space capsule heating, Thermal analysis of hypersonic vehicles|
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