飞船外形高超音速流场N-S方程数值解  

NUMBERICAL SOLUTION OF N-S EQUATIONS FOR HYPERSONIC FLOW OVER CAPSULE-TYPE VEHICLES

作　　者：周伟江[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《航空学报》1993年第1期A068-A071,共4页Acta Aeronautica et Astronautica Sinica

摘　　要：用二阶迎风TVD格式求解N-S访方程,对简化的飞船外形高超音速粘性绕流进行了数值模拟。给出了物面压力分布及流场结构,与实验及其他计算结果符合较好。计算表明,肩部圆弧半径对后体流场影响较小,但严重影响肩部附近热流分布。当肩部圆弧半径是头部半径的20％时,肩部热流低干驻点处热流;半径为5％时,肩部热流超过驻点处热流30％。The laminar N-S equations are solved for hypersonic flow over capsule-typere-entry vehicles by using the second-order windward TVD scheme. The detail flow-field structures and pressure distribution along body, surface are given, and its good agreement with experiment and reference is reached. The calcultions also show that the variation of raddius R2 dose not cause much flowfield change on the afterbody, but it has a great effect on the heating rate near the shoulder. In the case of R2 = 0.2, heating rate peak on the shoulder is slightly less than the stagnation values; however, when R2is, equal to 0.05, this peak is much higher and exceeds the stagnation value by 30%.

关 键 词：高超音速流动 数值模拟 飞船 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]