An investigation of possible Shuttle upgrades using advanced TPS concepts
暂无分享，去创建一个
[1] Graham V. Candler,et al. Review of Chemical-Kinetic Problems of Future NASA Missions, II: Mars Entries , 1993 .
[2] F. Milos,et al. Solution strategy for thermal response of nonablating thermal protection systems at hypersonic speeds , 1996 .
[3] Dave Olynick,et al. Trajectory based TPS sizing for an X-33 winged vehicle concept , 1997 .
[4] W. Pitts,et al. Reusable surface insulations for reentry spacecraft , 1991 .
[5] Peter A. Gnoffo,et al. Multiblock analysis for Shuttle Orbiter reentry heating from Mach 24 to Mach 12 , 1994 .
[6] C. Wilke. A Viscosity Equation for Gas Mixtures , 1950 .
[7] David R. Olynick,et al. Importance of 3-D grid resolution and structure for calculating reentry heating environments , 1996 .
[8] H. Lomax,et al. Thin-layer approximation and algebraic model for separated turbulent flows , 1978 .
[9] C. Park,et al. Nonequilibrium Hypersonic Aerothermodynamics , 1989 .
[10] David R. Olynick,et al. Aerothermodynamic heating analysis and heatshield design of an SSTO rocket vehicle for Access-to-Space , 1995 .
[11] David R. Olynick,et al. Navier-Stokes Heating Calculations for Benchmark Thermal Protection System Sizing , 1996 .