风洞自由飞实验测量M=5，10^o半锥角尖锥、钝锥气动动稳定特性  

Measurement of aerodynamic dynamic stability characters of M = 5 pointed and blunted cones with semi-cone angles equal 10^o in wind tunnel free flight experiment

作　　者：贾区耀[1] 杨益农[1] 陈农[1] 

机构地区：[1]航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2007年第B12期24-28,共5页Acta Aerodynamica Sinica

摘　　要：超声速、高超声速小攻角状态下简单尖锥体、小钝锥体外形的飞行器能否产生锥动失稳是一个可以讨论的命题。但是简单尖锥体、小钝锥体我们的风洞自由飞实验结果（M=5）：会产生锥动失稳，甚至实验次数中出现锥动失稳的比例达100％。借助近十年来对多个飞行器锥动失稳的研究（这些飞行器外形变化、流场参数变化、对锥动失稳的影响，模型风洞自由飞实验结果与飞行器空中飞行结果取得一致）观察到一个现象：改变飞行器尾部流动状态，有利于控制锥动失稳。简单10^o半锥角尖锥体、小钝锥体模型在锥体后部表面加上小片条后，锥动失稳（M=5）得到控制。Simple pointed cone and small blunted cone aircrafts when in supersonic, hypersonic and small attack angle conditions produce conical destabilization or not is a subject worth discussing. Our wind tunnel free fight experiment results show that this kind of shape when M = 5 generates conical destabilization, and its occurrence rate reaches 100%. With our study of conical destabilization with several aircrafts in latest ten years, a phenomenon is observed ： changing trailing flowage of aircrafts is beneficial to control of conical destabilization. Simple pointed cone and small blunted cone aircrafts with semicone angles 10^o, after adding small edges on the tail of cone surface, conical destabilization （ M = 5） is successfully controlled.

关 键 词：流动控制 尖 钝锥体锥动失稳 风洞自由飞实验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]