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机构地区:[1]北京理工大学机电工程学院,013博北京100081
出 处:《宇航学报》2004年第2期131-134,共4页Journal of Astronautics
摘 要:导弹飞行时,由发动机喷出的高温高速燃气射流对周围的空气流场产生强烈的扰动作用,从而影响导弹的空气动力特性,但由于燃气射流的存在,采用实验方法对燃气射流气动干扰进行估计有很大难度。本文采用三维流场数值模拟方法,模拟导弹弹体中部斜喷管燃气射流和空气耦合流场,对斜置喷管燃气射流空气动力干扰进行了研究。结果表明:斜置喷管燃气射流的存在,使导弹气动力的阻力增大,升力降低。The aerodynamic characteristics were disturbed intensively when jet flow exhausted from the nozzle to air flow. However, as the existence of jet flow, the investigation of the aerodynamic interference was very complicated. In the thesis, a numerical scheme for flow field of three dimensions was used to simulate the coupled flow field between jet flow and air flow. The aerodynamic interference of jet flow exhausted from canted nozzle which was fitted in the middle of missile was studied. As a result, the existence of jet flow of the canted nozzle make dynamic characteristics increase the drag coefficient and decrease the lift coefficient.
分 类 号:V411.4[航空宇航科学与技术—航空宇航推进理论与工程]
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