摘要
以二波系轴对称外压式超声进气道为例,说明进气道在亚临界工作状态下的脱体激波位置和附加阻力系数的英美计算方法及俄罗斯的附加阻力系数计算方法,两种方法的计算结果与实验数据的比较表明了该算法的有效性,并对两种算法的特点进行了比较和分析。
UK and US calculating methods of detached shock wave position and additive drag coefficient, for the example of axisymmetric supersonic inlet, are introduced under subcritical operating condition and Russian method of additive drag coefficient is also provided in the paper. The results have shown that the methods are validated. In addition, the methods are contrastively analyzed.
出处
《航空发动机》
2002年第3期42-46,共5页
Aeroengine
