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弹箭与制导学报 >

2017 , Vol. 37 >Issue 4: 113 - 116

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2017.04.027

弹道与气动力技术

后缘可变弯度翼型在跨声速中气动特性分析

  • 林义彪 ,
  • 马贵春 ,
  • 符文科 ,
  • 王迎
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  • 中北大学机电工程学院,太原 030051

林义彪(1989-),男,山东菏泽人,硕士研究生,研究方向:可变性机翼结构设计及气动特性分析。

收稿日期: 2016-12-02

  网络出版日期: 2025-05-28

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Analysis of Dynamic Characteristics of Trailing Edge Variable Camber Airfoil in Transonic

  • LIN Yibiao ,
  • MA Guichun ,
  • FU Wenke ,
  • WANG Ying
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  • School of Mechatronics Engineering, North University of China, Taiyuan 030051, China

Received date: 2016-12-02

  Online published: 2025-05-28

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摘要

为了研究后缘可变弯度翼型在跨声速中应用,对超临界翼型DFVLRR-4翼型后缘弯度向下分别偏转1°、2°、3°,得到3种变形翼型,对其进行跨声速下气动力数值研究。结果表明:随着后缘弯度增加,翼型的临界马赫数提前,阻力发散特性变差,但其升力系数增加以及激波失速前升阻比增加,且翼型的失速迎角特性得到改善;翼型变化量在1°时,在跨声速中的气动特性较好,翼型升力系数提高了21.12%,升阻比提高9.2%。得出后缘可变弯度翼型能够较好的运用到跨声速中。

关键词： 超临界翼型; 可变弯度; 跨声速; 阻力发散特性; 升阻比; 失速迎角

本文引用格式

林义彪 , 马贵春 , 符文科 , 王迎 . 后缘可变弯度翼型在跨声速中气动特性分析[J]. 弹箭与制导学报, 2017 , 37(4) : 113 -116 . DOI: 10.15892/j.cnki.djzdxb.2017.04.027

Abstract

In order to study the application of trailing edge variable camber airfoil in transonic, the supercritical airfoil DFVLR R-4 trailing edge camber was deflected downward 1º, 2º, 3º respectively. Three kinds of deformed airfoils were derived, and the study of aerodynamic numerical value in transonic was carried out. The results showed that with the increase of trailing edge camber, the critical Mach number of airfoil was advanced, and the resistance divergence characteristics deteriorated, but its lift coefficient and lift drag ratio before shock stall increased, and the characteristics of airfoil stall angle of incidence were improved. When the airfoil variation was at 1°, the aerodynamic characteristics in transonic was preferable, while the lift coefficient of airfoil and the lift drag ratio increased by 21.12% and 9.2% respectively. The trailing edge variable camber airfoil could be well applied to transonic.

Key words： supercritical airfoil; variable camber; transonic speed; resistance divergence characteristics; lift drag ratio; stall angle of incidence

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