特殊大气环境下格尼襟翼的气动特性

崔钊; 谢强; 张华; 韩东; 李建波

doi:10.7638/kqdlxxb-2017.0190

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特殊大气环境下格尼襟翼的气动特性

研究论文 | 更新时间：2026-05-28

- 特殊大气环境下格尼襟翼的气动特性
- Aerodynamic characteristics of Gurney flaps under special atmosphere
- 空气动力学学报 2019年37卷第6期页码：908-914
- 作者机构：
  
  1. 中国飞行试验研究院飞机所,陕西,西安,710089
  2. 南京航空航天大学航空学院,江苏,南京,210016
- 作者简介：
  
  崔钊(1983-), 男, 陕西富平人, 高级工程师, 研究方向:主要从事旋翼空气动力学、直升机飞行试验研究.E-mail:hawkcz@nuaa.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0190
  中图分类号： V211.4
- 纸质出版：2019
- 稿件说明：
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崔钊, 谢强, 张华, 韩东, 李建波. 特殊大气环境下格尼襟翼的气动特性[J]. 空气动力学学报, 2019, 37(6): 908-914.

CUI Zhao, XIE Qiang, ZHANG Hua, et al. Aerodynamic characteristics of Gurney flaps under special atmosphere[J]. 2019, 37(6): 908-914.
崔钊, 谢强, 张华, 韩东, 李建波. 特殊大气环境下格尼襟翼的气动特性[J]. 空气动力学学报, 2019, 37(6): 908-914. DOI： 10.7638/kqdlxxb-2017.0190.

CUI Zhao, XIE Qiang, ZHANG Hua, et al. Aerodynamic characteristics of Gurney flaps under special atmosphere[J]. 2019, 37(6): 908-914. DOI： 10.7638/kqdlxxb-2017.0190.

摘要

临近空间飞行器和火星探测飞行器首要面临低雷诺数、跨声速的特殊气动问题，针对此特殊环境下低雷诺数翼型的格尼襟翼增升方案，基于CFD方法开展了数值计算研究。对不同雷诺数、马赫数条件下，后缘加装不同高度格尼襟翼的Eppler387翼型的气动特性进行了对比分析，结果表明格尼襟翼增大了翼型的前缘吸力和后缘压差，从而显著增大了翼型环量和升力。在较高的马赫数下，格尼襟翼使翼型上表面低压区的范围扩大，对激波位置略有推迟。合适高度的格尼襟翼提高了翼型的最大升阻比，在中高升力系数下能够明显增大翼型的升阻比。研究结果能够为临近空间飞行器和火星探测飞行器的设计及改进提供技术支持。

Abstract

The low Reynolds number and transonic Mach regime posed severe challenges to near space vehicle and Mars exploration aircraft. The configuration with lift enhancement device known as Gurney flap (GF) was focused on

and the aerodynamic characteristics of GF under special environment was predicted based on CFD method. Aerodynamic characteristics of the Eppler387 airfoil with GF was analyzed for different Reynolds numbers

Mach numbers

and GF heights. The results indicated that the circulation of airfoil was increased significantly as well as the lift of airfoil

because the leading sucking peak and trailing edge pressure difference between upper and lower surface were enlarged. Under higher Mach number

lower pressure region on the upper surface of airfoil was expanded

and position of shock wave was slightly delayed. The maximum lift-to-drag ratio of the airfoil was improved by GF with appropriate height

and the lift-to-drag ratio was increased obviously under high lift status. The study can provide technical support to the design and improvement of the near space vehicle and Mars exploration aircraft.

关键词

Keywords

references

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