Recent advances in computational power enable computational fluid dynamic modeling of increasingly complex configurations. A review of grid generation methodologies implemented in support of the computational work performed for the X-38 and X-33 are presented. In strategizing topological constructs and blocking structures factors considered are the geometric configuration, optimal grid size, numerical algorithms, accuracy requirements, physics of the problem at hand, computational expense, and the available computer hardware. Also addressed are grid refinement strategies, the effects of wall spacing, and convergence. The significance of grid is demonstrated through a comparison of computational and experimental results of the aeroheating environment experienced by the X-38 vehicle. Special topics on grid generation strategies are also addressed to model control surface deflections, and material mapping. development and testing. Our involvement in the hypersonic vehicle design is to provide external aerodynamic and aerothermodynamic environments. The requirements for grid generation are determined from the simulation objectives. Aerodynamic simulations are required to determine the stability and controllability

Computational(_t,1)yrigId @211(11by th, hi|if i'll i_lt Institute (,f Aeronautics and Astr.nautics, In,. N,, ,:,q,yrigh( is asscrt(xl in the United States und, r Tith 17, II.S. (:(,,h. 'l'h( U.S.g.vernm_nt hasa r,yaltyt'r,_ li (_ns, t,, (xcr[isc MI rig.his under th(: c,, The ttow undergoes a pair of rapid expansions at the heatshield shoulder (point 1 in Fig. 5a) and the rearward facing step (point 2), which result in a local increase in heat transfer during the expansion, followed by a rapid decrease. An enlargement of the afterbody region is shown in Fig. 5b. The numbers in Fig. 5b correspond to the inset in Fig. 5a. The normal spacing was identical to the previous grid.From Fig. 6 .j" Kn¢;LL /-

No abstract

Computational(_t,1)yrigId @211(11by th, hi|if i'll i_lt Institute (,f Aeronautics and Astr.nautics, In,. N,, ,:,q,yrigh( is asscrt(xl in the United States und, r Tith 17, II.S. (:(,,h. 'l'h( U.S.g.vernm_nt hasa r,yaltyt'r,_ li (_ns, t,, (xcr[isc MI rig.his under th(: c,, The ttow undergoes a pair of rapid expansions at the heatshield shoulder (point 1 in Fig. 5a) and the rearward facing step (point 2), which result in a local increase in heat transfer during the expansion, followed by a rapid decrease. An enlargement of the afterbody region is shown in Fig. 5b. The numbers in Fig. 5b correspond to the inset in Fig. 5a. The normal spacing was identical to the previous grid.From Fig. 6 .j" Kn¢;LL /-

No abstract