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采用数值模拟方法,研究了高度H=0~35 km,Ma=0~4范围的助推器尾喷流对底部阻力的影响作用,获得了有、无尾喷流情况下底部阻力数据的变化规律。研究结果表明,在不同的高度、来流马赫数下,尾喷流对底阻的影响程度不同。与无喷状态的底阻相比,在低空、亚声速状态,尾喷流的抽吸引射效应较强,导致底部压力降低,底阻系数增大;在高空、超声速状态,外界大气压降低,尾喷流的膨胀角增大,导致底部压力增大,底阻系数降低;随着飞行高度进一步增大,外界大气压进一步降低,尾喷流充分膨胀,助推器尾喷流和外表面绕流干涉形成斜激波,助推器底部压力进一步增大,甚至形成附加推力。
The numerical simulation is used to study the influence of the rear jet on the drag at the height of H = 0 ~ 35 km and Ma = 0 ~ 4, and the change of bottom drag data with or without jet flow is obtained law. The results show that the effect of tail jet on the drag is different at different altitudes and Mach numbers. Compared with the non-sprayed bottom drag, the aspiration jet effect of the tail jet is stronger at lower and subsonic velocities, which leads to the decrease of the bottom pressure and the increase of the drag coefficient. At high altitude and supersonic velocity, the atmospheric pressure decreases and the tail As the swirling angle increases, the pressure at the bottom increases and the drag coefficient decreases. As the flight height further increases, the atmospheric pressure further decreases, the tail jet fully expands, and the rear jet and the outer surface flow around the booster interfere The formation of oblique shock, booster bottom pressure to further increase, and even the formation of additional thrust.