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热喷干扰气体模型对飞行器气动特性影响分析

傅杨奥骁 刘庆宗 丁明松 江涛 李鹏 董维中 许勇 高铁锁

傅杨奥骁, 刘庆宗, 丁明松, 江涛, 李鹏, 董维中, 许勇, 高铁锁. 热喷干扰气体模型对飞行器气动特性影响分析. 力学学报, 2022, 54(5): 1229-1241 doi: 10.6052/0459-1879-21-685
引用本文: 傅杨奥骁, 刘庆宗, 丁明松, 江涛, 李鹏, 董维中, 许勇, 高铁锁. 热喷干扰气体模型对飞行器气动特性影响分析. 力学学报, 2022, 54(5): 1229-1241 doi: 10.6052/0459-1879-21-685
Fu Yang’aoxiao, Liu Qingzong, Ding Mingsong, Jiang Tao, Li Peng, Dong Weizhong, Xu Yong, Gao Tiesuo. Analysis of gas model’s influence on aerodynamic characteristics for hypersonic vehicle over hot jet interaction flow field. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1229-1241 doi: 10.6052/0459-1879-21-685
Citation: Fu Yang’aoxiao, Liu Qingzong, Ding Mingsong, Jiang Tao, Li Peng, Dong Weizhong, Xu Yong, Gao Tiesuo. Analysis of gas model’s influence on aerodynamic characteristics for hypersonic vehicle over hot jet interaction flow field. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1229-1241 doi: 10.6052/0459-1879-21-685

热喷干扰气体模型对飞行器气动特性影响分析

doi: 10.6052/0459-1879-21-685
基金项目: 基础加强计划重点基础研究项目(2019-JCJQ-ZD-047)资助
详细信息
    作者简介:

    高铁锁, 研究员, 主要研究方向: 气动物理学及高温气体动力学. E-mail:gaots19654@163.com

  • 中图分类号: V211.751

ANALYSIS OF GAS MODEL’S INFLUENCE ON AERODYNAMIC CHARACTERISTICS FOR HYPERSONIC VEHICLE OVER HOT JET INTERACTION FLOW FIELD

  • 摘要: 针对不同气体模型对高超声速飞行器喷流反作用控制系统(RCS)热喷干扰流场模拟的计算效率和准确性问题, 基于喷流燃气物理化学模型, 通过数值求解含化学反应源项的三维N-S方程, 建立了飞行器RCS热喷干扰流场数值模拟方法, 分别采用化学反应流、反应冻结流、二元异质流以及空气喷流四种气体模型开展了典型外形热喷干扰流场的数值模拟, 研究了不同气体模型对热喷干扰流场结构、飞行器气动力热特性的影响, 分析了不同马赫数、飞行高度下的变化规律. 研究表明: 化学反应流模型计算精度较高, 计算与风洞试验数据的吻合程度优于其他三种简化模型; 在本文的低空条件下, 采用简化模型进行热喷干扰流场数值模拟, 会低估分离区大小, 使飞行器气动力特性预测出现偏差, 同时也会低估表面热环境, 对防热系统设计不利, 随着马赫数增加, 简化模型对气动力热特性预估的误差进一步增大, 同时不同简化模型之间的差异也进一步增大; 飞行高度较高时, 模型之间的差异减小, 此时可采用简化模型进行计算以提高计算效率. 本文的研究结果可为飞行器热喷干扰流场数值模拟及喷流反作用控制系统设计提供参考.

     

  • 图  1  试验模型外形

    Figure  1.  Configuration of the test model

    图  2  流场参数分布云图

    Figure  2.  Flow field parameters distribution contour

    图  3  模型表面表面压力系数分布对比

    Figure  3.  Comparison of surface pressure coefficient distribution

    图  4  计算网格

    Figure  4.  Sketch of computation grid

    图  5  不同网格得到的热流分布对比

    Figure  5.  Comparison of heat flux

    图  6  模型表面压力系数分布对比

    Figure  6.  Comparison of surface pressure coefficient distribution

    图  7  表面压力分布对比

    Figure  7.  Comparison of surface pressure distribution

    图  8  喷口附近的组分质量分数分布对比

    Figure  8.  Species mass fraction distribution near nozzle outlet

    图  9  上表面对称线上热流分布对比

    Figure  9.  Comparison of heat flux distribution along upper side symmetric line

    图  10  不同气体模型的计算效率对比

    Figure  10.  Comparison of efficiency for different model

    图  11  不同马赫数下的气动力热特性对比(H = 20 km, a = 0°)

    Figure  11.  Comparison of aerodynamic and aerothermal characteristics for different flight Mach number(H = 20 km, a = 0°)

    图  12  反应冻结流温度云图对比(H = 20 km, a = 0°)

    Figure  12.  Comparison of specific heat ratio contour for chemical frozen flow (H = 20 km, a = 0°)

    图  13  反应冻结流比热比云图对比(H = 20 km, a = 0°)

    Figure  13.  Comparison of specific heat ratio contour for chemical frozen flow (H = 20 km, a = 0°)

    图  14  不同高度下的气动力热特性对比(Ma = 5, a = 0°)

    Figure  14.  Comparison of aerodynamic and aerothermal characteristics for different flight altitude(Ma = 5, a = 0°)

    15  不同高度下的气动力热特性对比(Ma = 10, a = 0°)

    15.  Comparison of aerodynamic and aerothermal characteristics for different flight altitude(Ma = 10, a = 0°)

    表  1  化学反应模型

    Table  1.   Chemical reaction model

    No.ReactionNo.Reaction
    1 CO2 + M1↔CO + O + M1 11 NO + CO ↔ CO2 + N
    2 H2O + M2↔H + OH + M2 12 CO2 + O ↔ O2 + CO
    3 CO + M3 ↔C + O + M3 13 CO + CO ↔ CO2 + C
    4 N2 + M4 ↔N + N + M4 14 CO + O ↔ O2 + C
    5 O2 + M5 ↔O + O + M5 15 CO + N ↔NO + C
    6 NO + M6 ↔N + O + M6 16 OH + CO ↔CO2 + H
    7 H2 + M7 ↔H + H + M7 17 OH + H2 ↔H2O + H
    8 OH + M8 ↔O + H + M8 18 H + O2 ↔OH + O
    9 O + NO ↔N + O2 19 O + H2 ↔OH + H
    10 O + N2 ↔N + NO 20 OH + OH ↔H2O + O
    下载: 导出CSV

    表  2  喷管出口燃气组分质量分数

    Table  2.   Hot gas species mass fraction at nozzle exit

    CO2H2OCON2O2NO
    ci0.08670.29760.17440.41910.00020.0015
    H2OHCNHO
    ci0.01520.00497 e-111.1 e-60.00030.0001
    下载: 导出CSV

    表  3  不同网格计算得到的气动力系数对比

    Table  3.   Comparison of aerodynamic characteristics computed by different grid

    GridCoarseMediumDense
    CA0.14780.14800.1479
    CN−0.0158−0.0159−0.0159
    CMZ−0.0175−0.0176−0.0176
    下载: 导出CSV

    表  4  不同计算模型得到的气动力特性对比

    Table  4.   Comparison of aerodynamic characteristics by different gas model

    ReactingFrozBinaryAir
    CA0.14800.14820.15010.1472
    CN−0.0159−0.0047−0.0060−0.0030
    CMZ−0.0176−0.0227−0.0245−0.0251
    Fji/N−304.61−89.80−114.21−58.06
    Mji/(N·m)−337.70−433.89−468.92−480.33
    Kf1.04481.01321.01681.0085
    Km1.12871.16531.17861.1830
    下载: 导出CSV

    表  5  飞行器局部区域气动力系数对比

    Table  5.   Comparison of part aerodynamic coefficient

    CN, upCN, downCMZ, upstreamCMZ, downstream
    reacting−0.34540.3294−0.00214−0.01548
    froz−0.33280.3281−0.00168−0.02100
    binary−0.33230.3264−0.00181−0.02266
    air−0.33010.3271−0.00195−0.02311
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-12-24
  • 录用日期:  2022-03-29
  • 网络出版日期:  2022-03-30
  • 刊出日期:  2022-05-01

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