侧喷试验中喷口与模型间缝隙影响的数值研究  

Simulation of Missile with Gap between Jet and Missile in Lateral Jet Flowfield

作　　者：周培培[1] 郭少杰[1] 王斌[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《弹箭与制导学报》2016年第5期77-80,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中通过求解三维可压缩N-S方程,对超声速侧向单喷流干扰流场进行了数值模拟,验证了侧向喷流复杂流场数值模拟方法的可靠性。以此为基础,针对侧向喷流间接模拟风洞实验中喷口与模型存在缝隙的导弹外形,开展了数值模拟研究,分析了通气缝隙和不通气缝隙的流场结构。计算结果显示,缝隙通气与否对缝隙内的流动有明显影响,而对喷流干扰流场的影响比较小。For indirect simulation of lateral jet interaction in wind tunnel test, jet and test model are separated from each other with a thin gap. The lateral jet interaction field in supersonic flow was simulated by solving 3D, compressible N-S equations in this paper, comparison of CFD results with foreign experiment dates show that the numerical method is accurate and stable. Then the flow fields of lateral jet interaction for complex configuration with a thin gap were simulated. The internal flow fields of the thin gap were obtained, it was different between ventilated gap and unventilated gap, but the gap affected little on lateral jet interaction flow fields.

关 键 词：超声速流动 侧向喷流 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]