高超声速轴对称流道冷流特征及气动力特性研究

A study on the full flowpath and the aerodynamic characteristic of an axisymmetric hypersonic vehicle

对一种轴对称形式的高超声速飞行器全流道开展了风洞实验和数值模拟研究,分析了不同来流总压、飞行攻角全流道的流场结构和气动力特性.研究结果表明:(1)一定范围内雷诺数的变化对全流道的流动结构和模型的气动力特性无显著影响,因此所获得的风洞实验结果有望通过某种形式推广到飞行状态下使用;(2)飞行攻角对全流道的流动结构和升力系数有着显著影响,但阻力系数的影响并不明显;(3)研究范围内来流马赫数的变化对全流道的流动结构有着一定影响,但研究范围内,阻力系数随马赫数的变化幅度较小;(4)由于轴对称流道的浸润面积较大,研究范围内该类飞行器的摩擦阻力在全机阻力中占据了较大的比重,设计状态下达全机气动力的62%;(5)与实验结果的对照表明,所采用的数值模拟方法具有较高的精度.

Using the combined experiments and computational fluid dynamics （CFD）,a study was carried out to investigate the aerodynamic characteristics and the full flowpath of an axisymmetric hypersonic vehicle. Results indicate： （1） Over the tested range the Reynold number brings no obvious influence on the flow pattern and the aerodynamics characteristic of the hypersonic vehicle. （2） Despite the fact that the drag coefficient is not sensitive to the change of the angle of attack, the lift coefficient and the flow structure of the full flowpath is highly affected. （3） With the increase of the free stream Mach number,the drag coefficient fluctuates slightly though changes can be found in the full flowpath. （4） Over the tested flight conditions the friction drag of the axisymmetric hypersonic vehicle occupies a significant proportion of the total aerodynamic drag and at the design condition the proportion reaches 62%. （5） The experimental results prove the reliabilities of the CFD.