折叠舵外翼气动特性研究

刘小波; 阮文华; 齐治国; 司马坷; 彭忠良

doi:10.7638/kqdlxxb-2019.0057

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折叠舵外翼气动特性研究

研究论文 | 更新时间：2026-05-28

- 折叠舵外翼气动特性研究
- Study on aerodynamics of a folding wing
- 空气动力学学报 2021年39卷第1期页码：37-42, 51
- 作者机构：
  
  上海机电工程研究所,上海,201109
- 作者简介：
  
  刘小波(1986-), 男, 湖北汉川人, 高级工程师, 硕士, 研究方向: 飞行器气动布局设计. E-mail: liuwenqiang101@126.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2019.0057
  中图分类号： V211.3
- 纸质出版：2021
- 稿件说明：
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刘小波, 阮文华, 齐治国, 司马坷, 彭忠良. 折叠舵外翼气动特性研究[J]. 空气动力学学报, 2021, 39(1): 37-42, 51.

LIU Xiaobo, RUAN Wenhua, QI Zhiguo, et al. Study on aerodynamics of a folding wing[J]. 2021, 39(1): 37-42, 51.
刘小波, 阮文华, 齐治国, 司马坷, 彭忠良. 折叠舵外翼气动特性研究[J]. 空气动力学学报, 2021, 39(1): 37-42, 51. DOI： 10.7638/kqdlxxb-2019.0057.

LIU Xiaobo, RUAN Wenhua, QI Zhiguo, et al. Study on aerodynamics of a folding wing[J]. 2021, 39(1): 37-42, 51. DOI： 10.7638/kqdlxxb-2019.0057.

摘要

采用风洞试验和CFD相结合的方法对机载导弹折叠舵外翼气动特性进行了研究，研究内容包括外翼折叠角、迎角、来流

数、气动滚转角等，通过研究推导建立了外翼气动载荷的经验计算公式。研究结果表明，“×”型状态下外翼载荷随外翼展开而变大，在折叠角约30°附近载荷最大。CFD计算与试验数据吻合良好，不同

数下气动系数差别较小，

=1.2时气动系数值最大。大量计算数据表明，外翼气动载荷与当地气流偏角存在正相关性，并可以写成合成迎角，滚转角、舵面方位角和折叠角的函数。在迎风区预测值与样本值几乎完全重合，而在背风区受弹身干扰而存在一定误差。

Abstract

The aerodynamic characteristics of a folding wing of airborne missiles is investigated by wind tunnel experiments and computational fluid dynamics (CFD). The effects of the folding angle

the angle of attack (AoA)

the Mach number

the aerodynamic roll angle

etc. are inspected. We establish an empirical formula for the aerodynamic load on the outer wing. The CFD results agreed well with those in experiments. Results indicate that the aerodynamic force on the outer wing is proportional to its folding angle

with its maximum obtained around

=30°. The effect of the Mach number is the most evident at

=1.2

but it is generally small. Computational results show that the aerodynamic load on the outer wing is positive correlated with the local stream angle

and can be expressed as a function of the AoA

the roll angle

the position angle

and the folding angle. At the windward side

the predicted value agree well with the sample value

while at the leeward side

there were some errors due to the interfere of the missile body.

关键词

Keywords

references

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