高超声速再入飞行器气动特性的快速预示——局部方法的推广应用

Application of Local Method in Quick Prediction of Aerodynamic Characteristics of Reentry Vehicle in Hypersonic Flow

本文将计算高超声速稀薄气流过渡领域中气动特性的局部方法,推广应用到连续介质中弹头型高超声速再入飞行器气动力特性的快速估算。由激波风洞中M_∞=9.9时,一个8°钝锥的气动力测量结果,导出这一实验条件下的领域系数,并以此来估算不同锥角、不同钝度比及不同外形弹头型再入飞行器的气动力和力矩系数,其结果与无粘数值解及实验结果作了比较,在攻角2°～14°范围内吻合得很好。局部方法可用于弹头型高超声速再入飞行器气动特性的快速预示。

The paper widens the application of local method which used to be utilized in rarefied flow to the quick prediction of aerodynamic characteristics of missile-like reentry vehicle in hypersonic flow. The regime coefficients are drawn from experimental data of a 8?blunt cone at Mach 9.9. The aerodynamic coefficient predictions of blunt cones with different conical angle, bluntness and different configurations have been obtained using these regime coefficients. The comparisons of the predictions by local method with the data from invicid numerical results and experimental ones show a good agreement in the range of angles of attack from two degrees to fourteen degrees.