摘要
本文所提出的方法,是为了得到在超音速范围内钝头旋成体的压力分布,是由滞止区中的修正牛顿理论与表面流动变为超音速时的二次冲波—膨胀波理论所组成;以此导出了气动力系数的某些公式。
The paper presents a method to obtain the pressure distributions on blunt bodies of revolution in the supersonic-speed range. The method consists basically of a modified Newtonian theory for the stagnation region in correlation with the second-order shock-expansion theory when the surface flow becomes supersonic. The present method provides some formulae for the aerodynamic coefficien's.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
1990年第3期42-50,共9页
Acta Armamentarii
关键词
钝头旋成体
气动力系数
计算
blunt bodies of revolution, aerobynamic coefficient, pressure dissribution, modified Newtonian theory, second-order shock-expansion theory
