Influence of slot geometry configuration on airfoil aerodynamic characteristics

HAO Lishu; LIN Zijia; QU Haoyang; WANG Jianshu; GAO Yongwei

doi:10.7638/kqdlxxb-2022.0188

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Influence of slot geometry configuration on airfoil aerodynamic characteristics

更新时间：2026-05-28

- Influence of slot geometry configuration on airfoil aerodynamic characteristics
- Vol. 41, Issue 11, Pages: 36-45(2023)
- 作者机构：
  
  西北工业大学翼型叶栅空气动力学国家级重点实验室,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0188
  CLC： V211.3
- Published：2023
- 稿件说明：
移动端阅览
郝礼书, 林梓佳, 屈昊阳, 等. 缝道几何构型对翼型气动特性的影响[J]. 空气动力学学报, 2023, 41(11): 36−45.

HAO Lishu, LIN Zijia, QU Haoyang, et al. Influence of slot geometry configuration on airfoil aerodynamic characteristics[J]. 2023, 41(11): 36-45.
郝礼书, 林梓佳, 屈昊阳, 等. 缝道几何构型对翼型气动特性的影响[J]. 空气动力学学报, 2023, 41(11): 36−45. DOI： 10.7638/kqdlxxb-2022.0188

HAO Lishu, LIN Zijia, QU Haoyang, et al. Influence of slot geometry configuration on airfoil aerodynamic characteristics[J]. 2023, 41(11): 36-45. DOI： 10.7638/kqdlxxb-2022.0188.

摘要

为深入研究翼型开缝抑制翼型吸力面流动分离的被动流动控制技术，在探讨开缝依据的基础上，针对NACA 4421翼型设计了7种缝道构型，并给出了缝道构型之间的几何联系，对比分析了曲线、折线及直线3种形式的缝道对翼型失速的控制效果，发现曲线缝道能够显著提高翼型的最大升力系数和失速迎角；分析了曲线缝道构型升力系数“双峰”现象的机理，提出了一种新型导流片缝道构型，该构型利用“科恩达效应”能够全面改善基准翼型的失速特性，失速迎角推迟可达14°，最大升力系数提高122%，达到2.785，可为增升装置设计提供新的思路和参考。

Abstract

Airfoil slotted is a passive flow control technology that can effectively inhibit flow separation on the airfoil suction surface

and it has been widely studied by researchers domestically and abroad. In this study

slots on the airfoil NACA 4421 are investigated with numerical simulations. The selection of the slot location on the airfoil is first analyzed

and the influence of the geometry change of the slot on the stall characteristics of the airfoil is discussed. Seven slot configurations are designed

and the geometric relations among them are given. The flow control effects of slots with curve lines

polylines and straight lines

on the airfoil stall are compared. It is found that the curve-line slot can significantly improve the maximum lift coefficient and the stall angle of attack of the airfoil. The "double peak" phenomenon of the lift coefficient distribution of the curve-line slot airfoil is analyzed

and the design of a new deflector slot is proposed. This new slot configuration is based on the Coanda effect

and can improve the stall characteristics of the baseline airfoil comprehensively

with the stall angle of attack delayed by 14° and the maximum lift coefficient increased by 122% to 2.785. The deflector slot presented in this study provides a novel idea and reference for the design of high-lift devices.

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Keywords

references

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