摘要
本文对杆形头部、圆筒尾部的弹丸模型进行了较系统的超音速(M=2.0,M=2.5)风洞试验;给出了试验曲线和典型流态的纹影照片,分析了杆形头部的气流分离过程、影响分离的因素以及两重分离和推后分离的产生,并提出了克服两重分离和推后分离的措施;初步探讨了杆形头部的稳定机理和一些设计问题。
An investigation has been made of the flow over a series of blunt shell models equipped with nose spike and cylindrical afterbody at Mach numbers of 2.0 and 2.5, and experimental data and shlieren photographs of typical flow behavions are obtained. The processes of flow separation of spiked blunt bodies and the factors influencing spike tip separation or retarded separation are discussed, and steps to prevent retarded separation are proposed. The mechanism of flight stability of spiked blunt bodies and some design problems are discussed.
出处
《兵工学报》
EI
CAS
1981年第4期53-63,共11页
Acta Armamentarii
