摘要
本文叙述高超音速飞行条件下多组元化学非平衡粘性激波层方程的数值计算,分析研究了有攻角钝头体再入飞行器三维流动,化学组元浓度,物面摩阻系数和气动加热率。流体介质为7个组元的电离空气,化学反应过程是以有限速率进行的。利用正交曲线坐标系的计算网格系统处理三维钝头体流场,应用有限差分法求解化学组元连续方程、ξ-动量方程,ξ-动量方程和能量方程。以上方程在计算坐标系中为二阶抛物型方程,采用隐式差分格式将每个差分方程化为元素三对角形式的线性方程组,在物面为完全催化壁的条件下进行求解。而将连续方程和法向动量方程两个一阶方程耦合在一起,化成块块三对角形式的方程组进行求解。对10°攻角的钝头体再入飞行器得出了三维数值计算结果。
This Paper describes hypersonic, nonequilibrium, Viscous shock-layer equation numerical calculation procedure for a multi-component mixture of reacting agases. In present work, three-Dimensional flowfields over the re-entry blunt bodies at high angle of attack, chemical specie mass fractions, skin-friction coefficient, and heat transfer rates are discussed. The viscous gas flows are considered to be seven-component Ionizing air. It is assumed that the chemical reactions proceed at finite rate, the chemical reactions proceed at finite rate. the present numerical method uses a general orthogonal cruve-coordinat computational grid system to treat three-dimensional blunt body flowfields. tne equations, including ξ-momentum, ζ-momentum, energy and species conservation equations, are solved by a finite-difference scheme.since these equations are second-order paraboilic in the computational corrdinate system, the element-tridiagonal system resulting from the paraboilc equations by an implicit finite-difference scheme gives the simultaneous linear algebraic equations which are solved for flows under a fully catalytic surface conditon. The block-tridiagonal system is derived from the continuity and normal momentum equations but they are coupled together and solved by a similar method. Three-dimensional computational results have been obtained for a re-entry blunt venicle at 10° angle of attack.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1992年第3期1-12,共12页
Journal of Astronautics
关键词
化学非平衡
粘性激波层
再入飞行器
Chemical nonequilibrium flow, Viscous shock-layer equation, Fully catalytic surface, Re-entry vehicle.
