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为研究来流攻角和喷流位置对横向喷流侧向控制力的影响,通过数值方法模拟了超声速条件下的横向喷流干扰流场,计算得到的壁面沿程压力分布与实验结果吻合良好.采用喷流力放大因子和实际作用位置表征喷流侧向控制力的实际作用效果,引入法向干扰力沿程增加系数来分析弹体表面的压力特征区域对侧向控制力的影响.计算结果表明:在喷流干扰下,侧向控制力大小不等于喷流设计推力,并带有绕喷流中心位置的低头力矩;低压尾迹区是影响侧向力实际作用效果的决定因素;攻角的增大和喷流位置的后移,分别有助于削弱低压尾迹区的干扰强度和作用范围,从而增强侧向控制力的实际作用效果.
In order to study the influence of the angle of attack and jet position on the lateral jet lateral control force, the jet flow field under the supersonic velocity was simulated by numerical method. The calculated pressure distribution along the wall was in good agreement with the experimental results The actual effect of jet lateral control force is represented by jet pressure amplification factor and actual position, and the effect of pressure characteristic area on the lateral control force is analyzed by introducing coefficient of increase of normal disturbance force along the way. The results show that the lateral control force is not equal to the jet design thrust with jet interference, and the bow torque is around the center of the jet. The LV wake region is the determinant of the actual effect of the lateral force. The angle of attack And the backward position of the jet flow respectively help to weaken the interference intensity and the range of action of the low-pressure wake region, thereby enhancing the actual effect of the lateral control force.