CAJ | 학술논문

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。
침대채용비원절면구형적탄체，개전고초성속기동특성화류장결구적수치모의연구，위선진고초성속비행기기동외형선형진행기술저비。연구결과표명，마혁수5~10범위내，여원형절면탄체상비，재공각5~15°범위내비원절면탄체승력계수증가27%~30%，이조력특성기본불변，재10°공각시최대승조비가체2.7~2.9；비원절면탄체영풍측정압력경대，배풍측분리구범위경대차존재교강적선와결구，치사배풍측부압력증가，종이산생교대적탄체승력。존재일정측활각적정황하，탄체전단배풍측비대칭선와류동결구，사비원절면탄체횡향정은정성증가。
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.