Unified Calculation of Hypersonic Flowfield for a Reentry Vehicle

A unified computational fluid dynamics (CFD) method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. With the use of this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C superorbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling the CFD code and the charring materials ablation code within a few iterations

[1]  C. Park.  Injection-induced turbulence in stagnation-point boundary layers , 1984 .

[2]  Takeharu Sakai,et al.  ASSESSMENT OF PLANCK-ROSSEL AND-GRAY MODEL FOR RADIATING SHOCK LAYER , 1997 .

[3]  Keisuke Sawada,et al.  Calculation of surface heat transfer for a sphere with wall injection , 1999 .

[4]  Michael E. Tauber,et al.  Heatshielding problems of planetary entry - A review , 1999 .

[5]  Harry Partridge,et al.  Chemical-kinetic parameters of hyperbolic Earth entry , 2000 .

[6]  Graham V. Candler,et al.  Review of Chemical-Kinetic Problems of Future NASA Missions, II: Mars Entries , 1993 .

[7]  Eishin Dendou,et al.  NUMERICAL SIMULATION OF HYPERSONIC FLOW OVER A SPHERE WITH SURFACE INJECTION , 1998 .

[8]  Keisuke Sawada,et al.  CFD calculation of heat fluxes in turbulent flow for Pioneer-Venus probes , 1998 .

[9]  Keisuke Sawada,et al.  Dynamics of pyrolysis gas in charring materials ablation , 1998 .

[10]  Satoshi Nonaka,et al.  Behavior of two-temperature model in intermediate hypersonic regime , 1999 .

[11]  Keisuke Sawada,et al.  Convergence issues on fully-coupled radiative gas dynamic calculations , 2000 .

[12]  Frank S. Milos,et al.  Galileo Probe Heat Shield Ablation Experiment , 1996 .

[13]  W. C. Pitts,et al.  Analysis of the Heat-Shield Experiment on the Pioneer-Venus Entry Probes , 1980 .

[14]  Scott Eberhardt,et al.  Diagonal implicit scheme for computing flows with finite rate chemistry , 1992 .

[15]  Keisuke Sawada,et al.  Calculation of Nonequilibrium Radiation from a Blunt-Body Shock Layer , 2001 .

[16]  Frank S. Milos,et al.  Computational equations for radiating and ablating shock layers , 1990 .

[17]  C. Park,et al.  Nonequilibrium Hypersonic Aerothermodynamics , 1989 .

[18]  F. S. Milos,et al.  Analysis of Galileo Probe Heatshield Ablation and Temperature Data , 1999 .