火星大气环境下加装格尼襟翼翼型的气动特性

陈柏仪; 张超群; 李建波

doi:10.7638/kqdlxxb-2024.0141

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火星大气环境下加装格尼襟翼翼型的气动特性

研究专栏——旋翼飞行器气动特性及其优化设计 | 更新时间：2026-05-28

- 火星大气环境下加装格尼襟翼翼型的气动特性
- Aerodynamic characteristics of airfoils with Gurney flaps in the Martian atmospheric environment
- 空气动力学学报 2025年43卷第3期页码：98-109
- 作者机构：
  
  南京航空航天大学直升机动力学全国重点实验室,南京,210016
- 作者简介：
  
  陈柏仪（2000—），女，广东潮州人，研究方向：旋翼空气动力学. E-mail：1602379357@qq.com
  李建波*，研究员，研究方向：直升机总体技术. E-mail：ljb101@nuaa.edu.cn
- 基金信息：
  
  中国科学院国家科学中心合作项目
- DOI：10.7638/kqdlxxb-2024.0141
  中图分类号： V275
- 纸质出版：2025
- 稿件说明：
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陈柏仪, 张超群, 李建波. 火星大气环境下加装格尼襟翼翼型的气动特性[J]. 空气动力学学报, 2025, 43(3): 98−109.

CHEN Baiyi, ZHANG Chaoqun, LI Jianbo. Aerodynamic characteristics of airfoils with Gurney flaps in the Martian atmospheric environment[J]. 2025, 43(3): 98-109.
陈柏仪, 张超群, 李建波. 火星大气环境下加装格尼襟翼翼型的气动特性[J]. 空气动力学学报, 2025, 43(3): 98−109. DOI： 10.7638/kqdlxxb-2024.0141

CHEN Baiyi, ZHANG Chaoqun, LI Jianbo. Aerodynamic characteristics of airfoils with Gurney flaps in the Martian atmospheric environment[J]. 2025, 43(3): 98-109. DOI： 10.7638/kqdlxxb-2024.0141.

摘要

火星大气稀薄、气候环境恶劣，旋翼在低雷诺数和高马赫数条件下工作，翼型后缘会产生非定常层流分离现象，气动性能下降。针对这一问题，提出后缘加装格尼襟翼的增升方案，采用CFD方法进行数值计算。以低雷诺数翼型CLF5605为研究对象，针对火星大气环境工况下的翼型进行气动特性计算，分析产生流动分离的原因；对不同雷诺数、马赫数和迎角下加装2%弦长的格尼襟翼的翼型进行气动特性计算，分析加装格尼襟翼对流场结构及气动性能的影响。研究发现：格尼襟翼可以有效抑制非定常层流分离现象，提高翼型的升力特性，但同时会产生一定的阻力，降低翼型的升阻比；在雷诺数

5000

～

20000

、迎角

= 0°～3°、马赫数低于0.65的范围内，格尼襟翼具有较好的增升特性。提出3种加装格尼襟翼的设计方案，计算旋翼的拉力、扭矩及悬停效率，并与干净旋翼对比分析，初步验证了格尼襟翼对火星无人机旋翼具有的一定增益效果，为后续火星无人机旋翼的设计优化提供了参考。

Abstract

Rotorcraft operating in the thin and cold Martian atmosphere typically encounter unique aerodynamic conditions characterized by low Reynolds numbers and high Mach numbers

resulting in degraded performance compared to Earth operations. This study investigated the aerodynamic characteristics of the CLF5605 low-Reynolds-number airfoil under Martian atmospheric conditions through three-dimensional unsteady incompressible Reynolds-averag

ed Navier-Stokes simulations using the

SST turbulence model. The analysis reveals unsteady laminar separation at the airfoil trailing edge

leading to periodic vortex formation and shedding

low-frequency lift and drag oscillations

and overall aerodynamic performance deterioration. To address these challenges

we proposed implementing Gurney flaps on the trailing edge. A comprehensive study was conducted to evaluate the aerodynamic performances of airfoils equipped with 2% chord-length Gurney flaps across varying Reynolds numbers

Mach numbers

and angles of attack. The results demonstrate that Gurney flaps effectively suppress unsteady laminar separation and enhance lift generation. However

their effectiveness is constrained to specific operational regimes: Reynolds numbers ranging from

5000

30000

Mach numbers below 0.65

and angles of attack between 0° and 3°. Additionally

while lift is improved

the lift-to-drag ratio remains unaffected due to proportional increases in drag. Furthermore

we developed and analyzed three Gurney flap-integrated rotor designs

which exhibited superior thrust generation

torque characteristics

and hovering efficiency compared to clean rotors. These findings provide critical insights and practical design guidelines for optimizing rotor performance of Mars unmanned aerial vehicles.

关键词

Keywords

references

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