高速风洞中大型飞机典型支撑方式干扰特性研究

李强; 刘大伟; 许新; 陈德华; 魏志

doi:10.7638/kqdlxxb-2016.0133

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

高速风洞中大型飞机典型支撑方式干扰特性研究

研究论文 | 更新时间：2026-05-28

- 高速风洞中大型飞机典型支撑方式干扰特性研究
- The study of interference characteristics of typical support struts on large aircraft in high-speed wind tunnels
- 空气动力学学报 2019年37卷第1期页码：68-74
- 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：
  
  李强(1990-), 男, 山东枣庄人, 硕士, 助理工程师, 研究方向:试验空气动力学.E-mail:Lq370402@163.com
  陈德华(1960-), 男, 四川南溪人, 博士, 研究员, 研究方向:试验空气动力学.E-mail:dehch@sina.com
- 基金信息：
  
  国家重点研发计划（2016YFB0200700）
- DOI：10.7638/kqdlxxb-2016.0133
  中图分类号： V211.7
- 纸质出版：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

CHEN D H, LIN J, GUO D P, et al. Technical ways to solve high speed key aerodynamic problems of large air transporters[J]. Experiments and Measurements in Fluid Mechanics, 2003, 18(2):1-5. (in Chinese)

WANG R, WU J, GUO Q, et al. Research on the affecting factors of test quality and improvement methods in 2.4 m transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(1):37-41. (in Chinese)

ZHANG B, WANG Y, DUAN Z, et al. Design method for large upswept afterbody of transport aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(10):1933-1939. (in Chinese)

WANG F X, et al. High speed wind tunnel test[D]. Beijing: National Defense Industry Press, 2003. (in Chinese)

CHENG H M. Interference and correction on wind tunnel testing[M]. Beijing:National Defense Industry Press, 2003. (in Chinese)

LI Q, LIU D W, CHEN D H, et al. Numerical investigation on the support interference of vane support system in high speed wind tunnels[C ] . 8 th National Fluid Dynamics Conference, 2014. (in Chinese)

WANG Y, LIU W, DENG X, et al. Computational investigation of sting interference in low speed pressurized wind tunnel[J]. Aircraft Design, 2009, 29(2):8-12. (in Chinese)

MASATAKA K. Wall and support interference corrections of NASA common research model wind tunnel tests in JAXA[R]. AIAA 2013-0963, 2013.

LYNCH F T. The crucial role of wall interference, support interference, and flow field measurements in the development of advanced aircraft configurations[R]. AGARD, 1993.

SU J, HUANG Y, LI Y, et al. Support interference of low-aspect-ratio flying-wing from subsonic to supersonic speed[J]. Acta Aerodynamica Sinica, 2015, 33(3):289-295. (in Chinese)

DUAN Z, WANG Y, PANG Y, et al. Numerical simulation of support interference on a tailless configuration[J]. Journal of Experiments in Fluid Mechanics, 2007, 21(4):13-17. (in Chinese)

WANG Y, HUANG T, DENG X. The study of aerodynamic characteristics of afterbody and effect of cable mounting[J]. Acta Mechanica Sinica, 2004, 36(3):257-264. (in Chinese)

XIONG N, LIN J, HE Z, et al. Study on the rear sting support interference for large transports configuration model in transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(2):51-55. (in Chinese)

ZHOU W, MA H, BAI P. The numerical study of effect by side sting on aerodynamic characteristics of wing-body configuration[J]. Journal of Astronautics, 2003, 24(6):617-620. (in Chinese)

LIU G Y, WANG R B, GUO Q T, et al. Wall parameters influence on centerline flow uniformity in 2.4 m transonic wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(9):2930-2938. (in Chinese)

YAN C, YU J, XU J, et al. On the achievements and prospects for the methods of computational fluid dynamics[J]. Advances in Mechanics, 2011, 41(5):562-589. (in Chinese)

LI Q. Investigation on the support interference characteristics and mechanism analysis of vane cable suspension support system in high speed wind tunnels[D]. Mianyang: China Aerodynamics Research and Development Center, 2015. (in Chinese).

LI X W, FAN X J, QIAO Z D. Collar grid and virtual grid methods in embedding technique[J]. Chinese Journal of Computation Physics, 2003, 20(2):111-118. (in Chinese)

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

经典跨声速翼型RAE2822数据分析

CHN-T1标模2.4米风洞气动特性试验研究

基于射流流动控制的飞翼布局飞行器阵风载荷减缓研究

基于风雷软件的壁面距离场的快速迭代并行求解方法

无人机气动/风能获取一体化设计