非圆截面弹体高超声速气动特性研究

摘要

The numerical simulation of aerodynamic characteristics and the flow field structure of noncircular cross section missile has been conducted in this paper. The results show that in the range of Ma5~10, the lift coefficient increases 27%~30%when the angle of attack is 5~15°, compared with that of circular cross section missile, while the drag coefficient changes little. The maximum lift-to-drag ratio is 2.7~2.9 when the angle of attack is 10°. The positive pressure on the windward side of the noncircular cross section increases. The value of negative pressure on the leeward side increases because of a larger separation zone. If there is angle of sideslip, the asymmetry flow structure on the leeward side will enhance the lateral stability.%针对采用非圆截面构型的弹体，开展高超声速气动特性和流场结构的数值模拟研究，为先进高超声速飞行器气动外形选型进行技术储备。研究结果表明，马赫数5~10范围内，与圆形截面弹体相比，在攻角5~15°范围内非圆截面弹体升力系数增加27%~30%，而阻力特性基本不变，在10°攻角时最大升阻比可达2.7~2.9；非圆截面弹体迎风侧正压力更大，背风侧分离区范围更大且存在较强的旋涡结构，致使背风侧负压力增加，从而产生较大的弹体升力。存在一定侧滑角的情况下，弹体前段背风侧非对称旋涡流动结构，使非圆截面弹体横向静稳定性增加。