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吸气式飞行器连续变马赫数风洞试验技术

周健 张江 陈强 魏巍 刘磊 钱丹丹

周健, 张江, 陈强, 等. 吸气式飞行器连续变马赫数风洞试验技术[J]. 实验流体力学, 2023, 37(6): 76-85 doi: 10.11729/syltlx20210189
引用本文: 周健, 张江, 陈强, 等. 吸气式飞行器连续变马赫数风洞试验技术[J]. 实验流体力学, 2023, 37(6): 76-85 doi: 10.11729/syltlx20210189
ZHOU J, ZHANG J, CHEN Q, et al. Wind tunnel test technique of continuous varying Mach number for air-breathing vehicle[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(6): 76-85 doi: 10.11729/syltlx20210189
Citation: ZHOU J, ZHANG J, CHEN Q, et al. Wind tunnel test technique of continuous varying Mach number for air-breathing vehicle[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(6): 76-85 doi: 10.11729/syltlx20210189

吸气式飞行器连续变马赫数风洞试验技术

doi: 10.11729/syltlx20210189
详细信息
    作者简介:

    周健:(1988—),男,河北沧州人,硕士研究生,高级工程师。研究方向:试验流体力学。通信地址:北京市丰台区云岗西路17号7201信箱12分箱(100074)。E-mail:buaazhouj@163.com

    通讯作者:

    E-mail:13611319903@163.com

  • 中图分类号: V231.3

Wind tunnel test technique of continuous varying Mach number for air-breathing vehicle

  • 摘要: 为研究吸气式飞行器加/减速引起的进气道起动/再起动现象,以及该过程导致的飞行器整体气动性能突变问题,基于二维楔面激波机理,在1.2 m量级风洞中开展了超声速连续变马赫数试验技术研究,通过研制激波发生与控制系统,实现了一次风洞试验过程中马赫数连续可调。该技术方案具有马赫数调节简单、响应快,马赫数控制可靠、精度高等特点。流场校测表明,瞬时变马赫数区域流场品质满足国军标要求,可开展基于马赫数连续变化的测力测压等风洞试验。在进气道动态特性验证试验中,成功捕获了连续减速状态下进气道由起动到不起动的动态过程,临界状态特性与仿真结果一致性较高。
  • 图  1  连续变马赫数原理图

    Figure  1.  Diagram of continuous varying Mach number

    图  2  波后马赫数随δ变化曲线

    Figure  2.  Curve of Mach number after shock wave with δ

    图  3  FD–12风洞照片

    Figure  3.  Picture of FD–12 wind tunnel

    图  4  连续变马赫数试验段内芯

    Figure  4.  Inner core of continuous varying Mach number test section

    图  5  喷管出口速度型

    Figure  5.  Velocity profiles at nozzle outlet

    图  6  上洞壁扩开角对流场的影响

    Figure  6.  Influence of expansion angle upper wall on flow field

    图  7  波后变马赫数流场气流偏斜角

    Figure  7.  Flow deflection angle of variable Mach number flow field behind shock wave

    图  8  激波板支持机构系统

    Figure  8.  Shock wave plate support mechanism system

    图  9  连续变马赫数试验流程

    Figure  9.  Test process of continuous varying Mach number

    图  10  测压耙安装图

    Figure  10.  Installation of piezometric rakes

    图  11  各激波板折角下马赫数分布云图

    Figure  11.  Cloud of Mach number on angles of δ

    图  12  变马赫数流场均匀区对比图

    Figure  12.  Comparison of actual and theoretical uniform flow field

    图  13  速度场校测结果

    Figure  13.  Calibration results of velocity flow-field

    图  14  AGARD–B标准模型

    Figure  14.  AGARD–B standard model

    图  15  方向场校测结果

    Figure  15.  Calibration results of directions flow-field

    图  16  进气道喉道压力脉动特性

    Figure  16.  Characteristics of dynamic pressure at inlet throat

    图  17  不同马赫数变化速率下内流道压力脉动特性

    Figure  17.  Characteristics of dynamic pressure with different rates of varying Mach number at internal flowpath

    图  18  进气道入口纹影图

    Figure  18.  Schlieren results of inlet

    图  19  进气道不起动导致的气动特性迟滞现象

    Figure  19.  Hysteresis of aerodynamic characteristics by inlet unstart

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出版历程
  • 收稿日期:  2021-12-20
  • 修回日期:  2022-01-17
  • 录用日期:  2022-01-20
  • 网络出版日期:  2022-11-15
  • 刊出日期:  2023-12-30

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