风洞非均匀流场中的一体化高超声速飞行器缩比模型气动性能研究  

Study of aerodynamic performance for integrated hypersonic vehicle's scaled model in the nonuniform flow fields of wind tunnel

作　　者：贺元元[1] 倪鸿礼[1] 郑中华[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2010年第4期44-47,共4页Journal of Experiments in Fluid Mechanics

摘　　要：准确预测气动推进性能是吸气式高超声速飞行器研究的重要挑战之一。针对CARDC吸气式高超声速实验室(AHL)自主设计的一体化高超声速飞行器风洞试验模型,通过数值模拟计算,研究了CARDC600mm脉冲燃烧风洞的流场,并与试验结果做了对比,确定了试验模型在风洞中的合理安装位置,分析了带舵面飞行器在进气道打开、发动机不工作情况下的气动性能,对比研究了试验模型部分处于风洞流场非均匀区时,风洞结果对模型气动性能产生的影响,对比了数值计算结果和风洞试验结果。结果为利用风洞试验结果准确分析飞行器气动性能提供了重要依据。The most significant challenge in the research of airbreathing hypersonic vehicle is to predict the aero-propulsive performance precisely.In this paper,the wind tunnel experimental model of integrated hypersonic vehicle designed by AHL（Airbreathing Hypersonic Laboratory） of CARDC is investigated with numerical method.The flow fields of 600mm impulse combustion wind tunnel of CARDC are studied numerically and compared with the experimental results.The reasonable installed position of experimental model is presented.The aerodynamic performance of the un-powered（inlet open but engine not working） model with attack angle and rudders is studied.The effects induced by the parts of model not put entirety in the uniform flow fields of the wind tunnel are also simulated and presented.These results provide the important evidences for analyzing the aerodynamic performance of vehicle precisely according to wind tunnel experimental results.

关 键 词：一体化高超声速飞行器 风洞 非均匀流场 数值计算 气动性能 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]