Importance of 3-D grid resolution and structure for calculating reentry heating environments

The effects of grid structure and resolution are investigated at reentry flow conditions for two 3-D geometries. Chemically reacting full Navier-Stokes calculations are generated around the shuttle orbiter at peak heating and compared with heating values derived from the STS-2 flight data. A number of grid configurations are employed to illustrate the effects of grid resolution and structure on the numerical heat transfer predictions. To isolate some of the effects of grid structure, 3-D calculations are carried out on an axisymmetric sphere-cone-cylinder. It is shown that windside heat transfer predictions which are in reasonable agreement with the flight data are obtained using 50 points normal to the body. The level of grid convergence in the direction normal to the surface relative to heat transfer is demonstrated by doubling the grid points in the normal direction. Further, it is concluded that the grid topology in the 3-D inviscid curved bow shock region strongly affects the prediction of numerical heat transfer. (Author)

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

[2]  Ethiraj Venkatapathy,et al.  The multidimensional self-adaptive grid code, SAGE , 1992 .

[3]  David R. Olynick,et al.  Aerothermodynamic heating analysis and heatshield design of an SSTO rocket vehicle for Access-to-Space , 1995 .

[4]  Dave Olynick,et al.  Trajectory based validation of the Shuttle heating environment , 1996 .

[5]  David R. Olynick,et al.  Navier-Stokes Heating Calculations for Benchmark Thermal Protection System Sizing , 1996 .

[6]  Peter A. Gnoffo,et al.  Solution Strategy for Three-Dimensional Configurations at Hypersonic Speeds , 1993 .

[7]  Pieter G. Buning,et al.  User's manual for the HYPGEN hyperbolic grid generator and the HGUI graphical user interface , 1993 .

[8]  P. Gnoffo.  An upwind-biased, point-implicit relaxation algorithm for viscous, compressible perfect-gas flows , 1990 .

[9]  Daniel J. Rasky,et al.  Review of numerical procedures for computational surface thermochemistry , 1994 .

[10]  C. Wilke.  A Viscosity Equation for Gas Mixtures , 1950 .

[11]  John Cleland,et al.  Thermal Protection System of the Space Shutt1e. , 1989 .

[12]  H. Goldstein,et al.  Reaction Cured Borosilicate Glass Coating for Low-Density Fibrous Silica Insulation , 1978 .

[13]  Peter A. Gnoffo,et al.  Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium , 1989 .

[14]  Peter A. Gnoffo,et al.  Multiblock analysis for Shuttle Orbiter reentry heating from Mach 24 to Mach 12 , 1994 .

[15]  Raymond Cosner.  CFD validation requirements for technology transition , 1995 .

[16]  Graham V. Candler,et al.  Comparison of coupled radiative flow solutions with Project Fire II flight data , 1995 .

[17]  F. Blottner,et al.  Chemically Reacting Viscous Flow Program for Multi-Component Gas Mixtures. , 1971 .