近空间高超声速弹箭气动数值模拟

Numerical Simulations for Aerodynamic Characteristics of Near Space Hypersonic Projectile

针对近空间高超声速飞行弹箭气动力、气动热问题,采用Spalart-Allmaras(SA)湍流模型和热完全气体模型,运用时间相关有限体积方法及AUSM+格式对三维非定常可压缩流体Navier-Stokes方程进行了数值模拟。再现了超高速条件下弹箭周围的复杂流动现象,得到热流分布规律,为进一步近空间超高速弹箭研究奠定了基础。计算结果表明阻力系数随着攻角的变化显著变大;弹箭尾翼气动加热很严重,弹箭尾翼变大时气动加热量明显增大,在设计弹箭时应引起足够重视。

Numerical simulations for the aerodynamic characteristics of near space hypersonic projectile have been computed using the Spalart - Allmaras （SA） turbulence model and thermally perfect model, a time - dependent, finite - volume numerical method and AUSM ^＋ scheme are adopted to solve the three dimensional Navier - Stokes equation. Numerical solutions of hypersonic projectile flow - field with attack angle are obtained, and the numerical results can be used in the further study of the near space hypersonic projectile and missile.