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超声速横向喷流侧向控制的数值模拟

李亚超 阎超 张翔 孟军

李亚超, 阎超, 张翔, 等 . 超声速横向喷流侧向控制的数值模拟[J]. 北京航空航天大学学报, 2015, 41(6): 1073-1079. doi: 10.13700/j.bh.1001-5965.2014.0398
引用本文: 李亚超, 阎超, 张翔, 等 . 超声速横向喷流侧向控制的数值模拟[J]. 北京航空航天大学学报, 2015, 41(6): 1073-1079. doi: 10.13700/j.bh.1001-5965.2014.0398
LI Yachao, YAN Chao, ZHANG Xiang, et al. Numerical simulation of lateral control in supersonic cross jet flow[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(6): 1073-1079. doi: 10.13700/j.bh.1001-5965.2014.0398(in Chinese)
Citation: LI Yachao, YAN Chao, ZHANG Xiang, et al. Numerical simulation of lateral control in supersonic cross jet flow[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(6): 1073-1079. doi: 10.13700/j.bh.1001-5965.2014.0398(in Chinese)

超声速横向喷流侧向控制的数值模拟

doi: 10.13700/j.bh.1001-5965.2014.0398
详细信息
    作者简介:

    李亚超(1989—),男,河南许昌人,硕士研究生,yachaoli@foxmail.com

    通讯作者:

    阎超(1962—),男,江苏徐州人,教授,yanchao@buaa.edu.cn,主要研究方向为高超声速空气动力学.

  • 中图分类号: V221+.3;TB553

Numerical simulation of lateral control in supersonic cross jet flow

  • 摘要: 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.

     

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出版历程
  • 收稿日期:  2014-07-03
  • 刊出日期:  2015-06-20

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