超声速横向喷流侧向控制的数值模拟

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. 

Numerical simulation of lateral control in supersonic cross jet flow

To investigate the effect of angle of attack and jet position on the lateral control force in the cross jet flow, the paper firstly simulated the supersonic cross jet flow by the numerical methods. The calculated longitudinal wall pressure distribution agreed well with the experimental results. Jet force amplification factor in longitudinal direction and center of interaction force were used to evaluate the actual performance of lateral control force in jet interaction. Moreover, normal interaction force accumulation coefficient was introduced to analyze how four characteristic areas on the body surface affect the lateral control force in jet interaction. The numerical results indicate that the lateral control force in jet interaction, which is equivalent to a normal force, together with a nose-down moment around center of jet, are not equal to the jet force in design. The wake zone of low pressure is a determinant factor affecting the actual performance of lateral control force. As the angle of attack increases, the strength of the interaction pressure in the wake zone decreases, which will enhance the lateral control force. With the jet location moving backward, the scope of the wake zone diminishes, which will improve the actual performance of lateral control force.