摘要
六种常规弹体在两种细长比下头部和尾部形状时CN,Xcp的影响进行实验研究，实验名义Mach数为4．0，4．5，5．0和6．0，a＝0°～6°（或0°～8°）。获得了一些对高超声速飞行器研制有实用价值的结果。
An Experimental studies for the six kind of general bodies with two fineness ratio had finished at the moderate hypersonic speeds.The test Mach numbers are 3.95, 4.57, 5. 17, and 5.88. The angles of attak are equal to 0－6°(or 0°-8°). The effects of the different nose and tai1 shapes on CN and Xcp and some important results for vehicle dasign and development are obtained.
出处
《空气动力学学报》
CSCD
北大核心
1997年第4期484-487,共4页
Acta Aerodynamica Sinica
关键词
导弹
头尾形状
气动特性
高超声速流
气动布局
missile body
Fineness ratio
aerodynamic characteristics
hypersonic flow
experimetation
