The study of interference characteristics of typical support struts on large aircraft in high-speed wind tunnels

LI Qiang; LIU Dawei; XU Xin; CHEN Dehua; WEI Zhi

doi:10.7638/kqdlxxb-2016.0133

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The study of interference characteristics of typical support struts on large aircraft in high-speed wind tunnels

更新时间：2026-05-28

- The study of interference characteristics of typical support struts on large aircraft in high-speed wind tunnels
- Vol. 37, Issue 1, Pages: 68-74(2019)
- 作者机构：
  
  1. 空气动力学国家重点实验室,四川,绵阳,621000
  2. 中国空气动力研究与发展中心高速空气动力研究所,四川,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2016.0133
  CLC： V211.7
- Published：2019
- 稿件说明：
移动端阅览
李强, 刘大伟, 许新, 陈德华, 魏志. 高速风洞中大型飞机典型支撑方式干扰特性研究[J]. 空气动力学学报, 2019, 37(1): 68-74.

LI Qiang, LIU Dawei, XU Xin, et al. The study of interference characteristics of typical support struts on large aircraft in high-speed wind tunnels[J]. 2019, 37(1): 68-74.
李强, 刘大伟, 许新, 陈德华, 魏志. 高速风洞中大型飞机典型支撑方式干扰特性研究[J]. 空气动力学学报, 2019, 37(1): 68-74. DOI： 10.7638/kqdlxxb-2016.0133.

LI Qiang, LIU Dawei, XU Xin, et al. The study of interference characteristics of typical support struts on large aircraft in high-speed wind tunnels[J]. 2019, 37(1): 68-74. DOI： 10.7638/kqdlxxb-2016.0133.

摘要

分析了大型飞机在高速风洞中常用的支撑形式（尾支撑、腹支撑和条带支撑）的干扰特性，比较了尾支撑干扰试验中辅助支撑装置的二次干扰量，为大型飞机高速风洞试验的支撑选择提供了参考依据。以Ty-154标模为研究对象，基于结构嵌套网格，通过数值求解Ty-154标模有、无支撑的气动特性获取了相应的支撑干扰量，分析了支撑干扰产生的机理。通过数值模拟尾支撑、腹支撑和条带支撑的组合状态，探索了辅助支撑装置的二次干扰影响。结果表明：数值模拟与试验结果吻合较好，研究结果可靠性高；尾支撑对试验模型的阻力和俯仰力矩系数干扰较大，条带支撑对试验模型的升阻特性干扰较小，腹支撑对试验模型的阻力系数干扰较大，对俯仰力矩系数干扰较小；

0.9时三种支撑形式的干扰量均迅速增加，腹支撑形式的干扰量增加最为剧烈；在尾支撑干扰修正试验中，腹支撑与条带支撑引起的二次干扰量均很小，工程应用可忽略。

Abstract

The interference characteristics of 3 different support struts commonly used in high speed wind tunnel tests for large aircraft are analyzed to provide some references in selecting support type

and the second-order interference characteristics caused by assistant support struts during sting interference test are also studied. Structural chimera grids are used to simulate Ty-154 standard model support by sting

belly blade and vane suspension

interference magnitudes are acquired respectively

and their interference mechanism is studied. Combination support type sting-blade and sting-vane are al

so simulated to investigate the second-order interference magnitude. The results show that numerical results coincide well with test data

proving the research results have a high fidelity. The sting support show much interference to the drag and pitching moment

while the vane support make little interference to them. The blade support make the drag increase much but shows little influence to the pitching moment. On the conditions of

0.9

the interference magnitude increase rapidly and the blade support increase the most. In the experiment of sting interference correction

the second-order interference of blade and vane support is very small

and can be omitted in the engineer field.

关键词

Keywords

references

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