摘要
采用DSMC方法对二维小尺度平板在近连续流至自由分子流区域、攻角为0°-30°下的高超声速气动特性进行计算分析，旨在探索高超声速飞行器在近空间空域内气动特性的变化规律和影响因素。结果表明，升阻比随努森数、马赫数的增加单调下降，相对比来说，马赫数对升阻比的影响不是很明显，而努森数的影响比较明显。特别针对摩阻特性进行了分析，在马赫数10、高度55-110km、0°攻角时摩阻在总阻力中所占比重高达60％以上。随着攻角的增加，由于波阻的急剧增加导致摩阻所占比重下降。在10°攻角下，摩阻在总阻力中所占比重约为45％-70％。30°攻角时摩阻在总阻力中所占比重则下降为12％-50％。同时还发现，在近自由分子流区域中，0°攻角时阻力系数随着马赫数的增加而下降，在有攻角时该马赫数效应呈现减弱趋势。
Hypersonic aerodynamics of flat plate with sharp leading edge flying from continuum flow regime to near free molecule flow regime at angle of attack from 0° to 30°has been analyzed with DSMC approach. The purpose of this study is to investi-gate the aerodynamics of hypersonic vehicle in the near space. The results show that the ratio of Lift-to-Total drag decrease as freestream Maeh number and Kn number increase. In this paper, special attention has been paid to friction drag. The ratio of Friction-to-Total drag is over 60% at Mach 10,0° angle of attack and the altitude range from 55km to 110km. As angle of attack increasing, pressure drag increases, which lead to decrease of the ratio of Friction-to-Total drag. The ratio of Friction-to-Total drag is about 45%-70% at 10° angle of attack, and about 12% - 50% at 30° angle of attack. Drag coefficient decreases near free molecule flow regime as Mach number increase at 0° angle of attack.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2009年第3期900-907,共8页
Journal of Astronautics
