文档介绍：May 11, 2004 DP - 7
REACTING FLOW ENVIRONMENTS BRANCH ELORET
DECOUPLING FLOW & MATERIAL RESPONSE
解耦流及材料反应
TPS materials not selected at the preliminary design phase - computations should guide this choice
初始设计阶段未选择防热系统材料-计算应引导至此选择
Assume that the surface is non-conducting and can only re-radiate 一 adiabatic back wall assumption
假设表面无传导性，只有再辐射性-隔热后墙假设
Assume that the surface promotes complete recombination of atoms reaching it - conservative assumption because maximum heat release can be expected
假设表面促使到达表面的原子完全重组-保守假设从而得出最大散热
Aerothermal analysis can now be performed with a steady flow assumption at any trajectory point 一 time discretization
气动热分析只能在稳定流场假设下的任意轨道点进行-时间离散化
•Time discretization cannot be too fine for CFD computations - enormous number of computations required
时间离散化不太适用于CFD计算-需要对大量数据进行计算
Need to supplement CFD computations with engineering methodology of acceptable accuracy - engineering methods are much quicker 需要使用合适精准度的工程学方法补充CFD计算-工程学方法更为快速
M 町 11, 2004 DP - 8
REACTING FLOW ENVIRONMENTS BRANCH ELORET
ABOUT THIS PRESENTATION 关于此次演示
To demonstrate the combination of CFD and engineering methodology in defining aerothermal environments for TPS design
演示为防热设计所定义的气动热环境下的CFD与工程学方法的结合
Assumes Earth atmospheric flight 一 flow medium consists of N2, 02, & products
假设地球大气层飞行-气场至少包含氮气、氧气及其化合物
Does not call out material choices or sizing
不涉及材料选择及大小
Uses X-33 flight vehicle as a case study
使用X-33飞行器作为案例研究
The presentation is not a comprehensive account of various approaches
此演示非多种方法的综合预计
The presentation is a focused one 一 drawn on the experience of a small team at NASA Ames Research Center
此次演示为一次集中演示-由NASA阿姆斯研究中心一个小组经验绘出
May 11, 2004 DP - 9
REACTING FLOW ENVIRONMENTS BRANCH ELORET
REQUIREMENTS - CONFIGURATION
要求-结构
Since in-depth conduction is neglected, only the outer surface (outer mold line or OML) definition is required
由于已忽略深度传导性问题，此处只要求对外表(外模线，又称OML)做出定义
Configuration is usually available in some CAD format
在一些CAD公式中可