水下亚声速细长锥型射弹超空泡形态的计算方法

采用理想可压缩流体无旋定常流动以及超空泡尾部Riabushinsky闭合方式假定,基于细长体理论和匹配渐近展开法,建立了描述水下亚声速条件下细长锥型射弹超空泡流动的积分微分方程。求解得到了考虑压缩性影响的超空泡形态1阶和2阶近似解,改进了超空泡形态的计算精度。分析了射弹高速冲击条件下流体压缩性对超空泡形态的影响,随着马赫数的增加,超空泡形态将发生更加显著的膨胀变化。计算得到的超空泡特征参数与相关文献的理论和实验结果吻合良好。

A calculation method for supercavity profile about a slender cone-shaped projectile traveling in water at subsonic speed

By adopting the irrotational and steady motion of the ideal compressible fluid and the supercavity with the Riabushinsky scheme of closure,an integro-differential equation was derived for the supercavitating flow around a slender cone-shaped projectile traveling in water at subsonic speed by using the slender-body theory and the matched-asymptotic-expansions method. The first-and second-order approximation solutions for the supercavity shapes considering the compressibility effect were obtained,and the calculation precision was improved. The influences of the flow compressibility on the supercavity profiles were analyzed under the high-speed impact of the gun-launched projectile. With the increase of Mach number,the supercavity shape expands markedly. The calculated characteristic parameters for the supercavity profiles are in agreement with the theoretical and experimental results.