适用于多迎角结冰试验的混合翼型设计

于雷; 杨龙; 朱东宇

doi:10.7638/kqdlxxb-2019.0071

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适用于多迎角结冰试验的混合翼型设计

研究论文 | 更新时间：2026-05-28

- 适用于多迎角结冰试验的混合翼型设计
- Hybrid airfoil design method for multi-angle of attack condition in icing wind tunnels
- 空气动力学学报 2021年39卷第1期页码：66-72
- 作者机构：
  
  中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点试验室,沈阳,110034
- 作者简介：
  
  于雷(1987-), 男, 汉族, 吉林大安人, 高级工程师, 研究方向: 飞机结冰.E-mail: aerowater@163.com
- 基金信息：
  
  国防基础科研计划（JCKY2016205C012）
- DOI：10.7638/kqdlxxb-2019.0071
  中图分类号： V211.71
- 纸质出版：2021
- 稿件说明：
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于雷, 杨龙, 朱东宇. 适用于多迎角结冰试验的混合翼型设计[J]. 空气动力学学报, 2021, 39(1): 66-72.

YU Lei, YANG Long, ZHU Dongyu. Hybrid airfoil design method for multi-angle of attack condition in icing wind tunnels[J]. 2021, 39(1): 66-72.
于雷, 杨龙, 朱东宇. 适用于多迎角结冰试验的混合翼型设计[J]. 空气动力学学报, 2021, 39(1): 66-72. DOI： 10.7638/kqdlxxb-2019.0071.

YU Lei, YANG Long, ZHU Dongyu. Hybrid airfoil design method for multi-angle of attack condition in icing wind tunnels[J]. 2021, 39(1): 66-72. DOI： 10.7638/kqdlxxb-2019.0071.

摘要

为突破结冰风洞对翼型模型尺寸的限制，提出了一种新的混合翼型设计方法，可使用一套混合翼型模拟原始翼型在不同迎角下的结冰试验，弥补了以往混合翼型只能在单个设计迎角下使用的缺陷。方法采用多段翼的形式设计混合翼型，以多目标迎角等结冰试验条件作为设计输入，优化设计主翼外形和襟翼的位置、偏转角度，利用襟翼位置和偏转角度的变化实现混合翼型和原始翼型前缘表面的压力系数在不同迎角下能够保持一致，继而保证前缘结冰外形的一致性。设计的混合翼型较原始翼型弦长减小接近40%，在冰风洞中对混合翼型和原始翼型在目标结冰条件下进行试验，对比结果显示，在选取的多个目标迎角下，混合翼型和原始翼型二维截面的结冰外形基本一致，提出的混合翼型设计方法能够有效的模拟原始翼型在不同迎角下的结冰外形。

Abstract

To break through the limitation of airfoil size in icing wind tunnels

a new hybrid airfoil design method is proposed.Compared with other hybrid airfoil design methods

the most significant advantage of the present method lies in its capability to simulate the ice shapes of the original airfoil at different angles of attack with only one set of hybrid airfoil. This method is multi-element airfoil oriented. The shape of the main airfoil

and the position and deflection angle of the flap are designed according to the icing test conditions such as the angle of attack and so on. The change of the position and deflection angle of the flap ensures the consistency of the pressure on the nose section between the hybrid and original airfoils at different angles of attack

which in turn ensures the consistency of ice shapes on the nose section. The chord length of the obtained hybrid airfoil is nearly 40% smaller than that of the original one. Ice shapes of both the hybrid and original airfoils are acquired on two-dimensional airfoil models in an icing wind tunnel.Test results indicate that the ice shapes of the two-dimensional section of the hybrid airfoil are basically the same as those of the original airfoil at multiple angles of attack. Therefore

the proposed hybrid airfoil design method is effective to simulate the icing shape of the original airfoil at different angles of attack.

关键词

Keywords

references

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