采用HLLC近似黎曼解格式求解N-S方程,对大攻角条件下超音速尖拱细长旋成体导弹的单侧向喷流干扰流场进行了数值模拟。并对喷流流场压力分布、喷口附近流动及流场旋涡结构进行了研究,分析了大攻角对细长旋成体侧向喷流干扰压力分布及干扰因子的影响。研究结果表明,HLLC格式计算复杂流场具有较好的数值稳定性;侧向喷流与来流的干扰总体上对喷流直接力起抑制作用,消弱了喷流直接力的作用效果;流场对迎风面喷流干扰的抑制作用较背风面强,迎风面喷流干扰甚至出现完全抵消喷流直接力的结果,表现为喷流干扰因子Kf为负值的现象。 The HL-Ritz-Riemann solution was used to solve the N-S equation to simulate the unidirectional jet flow field of supersonic spire-long slingshot missile with large attack angle. The pressure distribution in the jet flow field, the flow around the nozzle and the vortex structure in the flow field were studied. The influence of the high angle of attack on the pressure distribution and the interference factor of the lateral jet flow in the slender body was analyzed. The results show that the computational complexity of the HLLC scheme has good numerical stability. The interference of the lateral jet and the incoming flow generally suppresses the direct jet force, which weakens the effect of jet direct force. Field on the windward jet interference suppression effect than the leeward, interference on the windward jet or even completely counteract the direct jet force results, manifested as jet interference factor Kf is a negative phenomenon.