转速对高速旋转冲压增程弹用进气道影响数值模拟

Numerical investigation for the effect of spinning velocity on high speed spinning ramjet assisted range projectile inlet

结合分区对接网格技术以及二阶精度区域分解算法,对高速旋转、含侧向支柱冲压增程弹丸进气道内外复杂流场进行了数值模拟。得到了高速旋转工况下对应于不同来流攻角和旋转角速度,临界工况时,超声速进气道内外流场复杂的波系结构。随着旋转角速度的提高,进气道总压恢复系数和动能效率均有所降低,而流场畸变指数则显著增大。特别是当转速达到20 kr/m in,进气道总压恢复系数和动能效率下降趋势以及流场畸变指数增大趋势更明显。攻角的存在对冲压发动机进气道的总体性能产生了负面影响。

By means of zonal patched grid technology and second-order zonal solver method, the numerical simulation on high speed spinning supersonic inlet complex flow field of solid rocket ramjet assisted range projectiles with struts was presented. Complex wave structures of supersonic inlet at different angle of attack and spinning velocity related to high speed spinning and critical status were achieved. As spinning velocity increases, both the total pressure recovery coefficient and the kinetic energy coefficient of inlet decrease and the flow distortion index increases obviously. Especially, when the spinning velocity is equal to 20 kr/min, the negative influence on overall performance of ramjet inlet is more obviously.