内流壁温效应对高速飞行器气动特性的影响

武利龙; 罗金玲; 李超; 肖志祥; 操小龙

doi:10.7638/kqdlxxb-2021.0273

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内流壁温效应对高速飞行器气动特性的影响

专栏——内外流一体化技术 | 更新时间：2026-05-28

- 内流壁温效应对高速飞行器气动特性的影响
- Effect of inner flow wall temperature on the aerodynamic characteristics of high-speed vehicles
- 空气动力学学报 2022年40卷第1期页码：84-91
- 作者机构：
  
  1. 北京机电工程研究所,北京,100074
  2. 北京空天技术研究所,北京,100074
  3. 清华大学航天航空学院,北京,100084
- 作者简介：
  
  武利龙*（1982-），河北邯郸人，高级工程师，研究方向：空气动力学，飞行器载荷设计，非结构化网格生成技术. E-mail：xjtullwu@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0273
  中图分类号： V411.4
- 纸质出版：2022
- 稿件说明：
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武利龙, 罗金玲, 李超, 等. 内流壁温效应对高速飞行器气动特性的影响[J]. 空气动力学学报, 2022, 40(1): 84−91.

WU Lilong, LUO Jinling, LI Chao, et al. Effect of inner flow wall temperature on the aerodynamic characteristics of high-speed vehicles[J]. 2022, 40(1): 84-91.
武利龙, 罗金玲, 李超, 等. 内流壁温效应对高速飞行器气动特性的影响[J]. 空气动力学学报, 2022, 40(1): 84−91. DOI： 10.7638/kqdlxxb-2021.0273

WU Lilong, LUO Jinling, LI Chao, et al. Effect of inner flow wall temperature on the aerodynamic characteristics of high-speed vehicles[J]. 2022, 40(1): 84-91. DOI： 10.7638/kqdlxxb-2021.0273.

摘要

吸气式高速飞行器内外流高度耦合，激波-边界层干扰严重，壁面温度会影响边界层内的流动，进而影响气动特性。因此，准确评估风洞试验中的壁温效应，提高气动特性的预测精度，对飞行器设计至关重要。通过常规超高速风洞试验，结合数值模拟分析，开展了内流壁温对气动特性的影响规律及作用机理研究。结果表明：在常规超高速风洞几十秒的运行时间内，随着运行时间增加，飞行器内流道壁面温度不断升高，俯仰力矩以及内流道壁面压力均会出现显著变化，其中俯仰力矩的增加量需要2°舵偏角来平衡；此外，数值模拟分析进一步指出，飞行器俯仰力矩的变化主要原因是内流道壁面温度升高、边界层增厚、近壁低速区挤压中心的高速区，使得内流道等效面积减小、气流压缩，相应的马赫数减小、压力升高，并引起内流道激波波系前移，从而改变了内流道压力分布，最终导致俯仰力矩发生变化。

Abstract

For air-breathing high-speed vehicles

inner and outer flows are highly coupled and there are strong interactions between shockwaves and boundary layers. Boundary layers are sensitive to the variation of the wall temperature

so do the aerodynamic characteristics. Consequently

how to predict the wall-temperature effect exactly and improve the prediction accuracy of aerodynamic characteristics are important for the design of high-speed vehicles. In this article

the effect of the inner flow wall temperature on aerodynamic characteristics is investigated through wind-tunnel measurements and numerical simulations. Results show that in conventional hypersonic wind tunnels

the inner wall temperature of the high-speed vehicle model increases continuously with the wind-tunnel running time

yielding significant variations of the pitching moment and wall pressure. The maximum increment of the pitching moment requires an increase of the rudder angle by 2°. In addition

numerical simulation results indicate that the thickness of boundary layer in the internal flow increases with the rise of wall temperature. Moreover

the equivalent area of high-speed flow channel decreases so that the flow is compressed. The change of velocity profiles in boundary layers results in the forward moving of shockwaves in the internal flow channel

which causes the change of pitching moment of high-speed vehicles.

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Keywords

references

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