飞机增升装置振荡射流增升减阻与降噪特性分析

郑少增; 严佳; 杨小权

doi:10.7638/kqdlxxb-2025.0018

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飞机增升装置振荡射流增升减阻与降噪特性分析

研究论文 | 更新时间：2026-07-11

- 飞机增升装置振荡射流增升减阻与降噪特性分析
- Analysis of lift enhancement, drag and noise reduction characteristics of oscillating jets on aircraft figh-lift devices
- 空气动力学学报 2026年44卷第6期页码：45-60
- 作者机构：
  
  上海大学力学与工程科学学院,上海,200072
- 作者简介：
  
  郑少增，研究方向：气动噪声. E-mail： 15964329355@163.com
  严佳*，研究方向：高精度数值方法与CFD软件开发. E-mail：yan_jia@shu.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0018
  中图分类号： V224+.5
- 纸质出版：2026
- 稿件说明：
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郑少增, 严佳, 杨小权. 飞机增升装置振荡射流增升减阻与降噪特性分析[J]. 空气动力学学报, 2026, 44(6): 45−60.

Zheng Shaozeng, Yan Jia, Yang Xiaoquan. Analysis of lift enhancement, drag and noise reduction characteristics of oscillating jets on aircraft figh-lift devices[J]. 2026, 44(6): 45-60.
郑少增, 严佳, 杨小权. 飞机增升装置振荡射流增升减阻与降噪特性分析[J]. 空气动力学学报, 2026, 44(6): 45−60. DOI： 10.7638/kqdlxxb-2025.0018

Zheng Shaozeng, Yan Jia, Yang Xiaoquan. Analysis of lift enhancement, drag and noise reduction characteristics of oscillating jets on aircraft figh-lift devices[J]. 2026, 44(6): 45-60. DOI： 10.7638/kqdlxxb-2025.0018.

摘要

针对飞机增升装置在起降阶段、中等迎角下襟翼流动分离引起的气动与噪声问题，本文以经典的30P30N三段翼模型为研究对象，在雷诺数为1.7×10

、马赫数为0.17、攻角为5.5°工况下，基于贝叶斯优化算法构建多参数寻优框架，发展了振荡射流增升减阻降噪方法，将改进延迟涡分离方法和FW-H（Ffowcs Williams-Hawkings）方程耦合，对混合气动力和气动噪声特性进行了数值模拟，在此基础上，对比了施加射流前后的流场特性。结果表明：频率为1倍特征频率、动量系数为1.897%、0.006%的振荡射流使30P30N后缘襟翼的分离涡明显减小，升力增加约8.24%，阻力下降约8.00%；气动噪声总声压级降低1.27 dB，在30°方向降幅最大，下降了2.88 dB，机翼正下方、距离模型5倍弦长处（270°

）的远场低频噪声下降了4.28 dB，脱落涡导致的纯音峰值下降幅度最大，达14.05 dB，高频噪声几乎不变。射流除直接向流场中注入能量外还通过引入扰动生成展向涡，促进了剪切层内低动量流体与主流高动量流体之间的能量交换，有效削弱了襟翼后缘的边界拟涡能流。这一过程显著减小了Lamb矢量散度的正负值相互作用区域，使该区域的声源强度得到抑制。本文研究可为飞机增升装置增升、减阻和降噪设计提供理论依据。

Abstract

This paper addresses the aerodynamic and noise issues caused by flap flow separation at moderate angles of attack during aircraft high-lift device takeoff and landing. Using the canonical 30P30N three-element airfoil as the research object

under conditions of Reynolds number 1.7×10

Mach number 0.17

and angle of attack 5.5°

a multi-parameter optimization framework based on Baye

sian optimization algorithm is established. An oscillating jet method for lift enhancement

drag reduction

and noise suppression is developed. The improved delayed detached-eddy simulation (IDDES) method is coupled with the Ffowcs Williams-Hawkings (FW-H) equation to numerically simulate the hybrid aerodynamic and aeroacoustic characteristics. Flow field properties with and without oscillating jet actuation are compared. Results indicate that oscillating jets with a frequency equal to the characteristic frequency and momentum coefficients of 1.897% and 0.006% significantly reduce the separation vortex on the trailing edge flap. Lift increases by approximately 8.24%

while drag decreases by about 8.00%. The overall sound pressure level (OASPL) of aerodynamic noise is reduced by 1.27 dB

with the maximum reduction of 2.88 dB observed at the 30° direction. At the far-field monitoring point directly beneath the wing at a distance of five chord lengths (270°

)

low-frequency noise decreases by 4.28 dB. The tonal peak caused by shed vortices exhibits the most substantial reduction of 14.05 dB

whereas high-frequency noise remains nearly unchanged. Beyond directly injecting energy into the flow field

the jet introduces disturbances that generate spanwise vortices

promoting energy exchange between low-momentum fluid within the shear layer and high-momentum fluid in the main stream. This process effectively weakens the boundary enstrophy flux at the flap trailing edge. Consequently

the interaction region of positive and negative Lamb vector divergence is significantly reduced

leading to suppressed acoustic source intensity in that zone. This study provides theoretical foundations for lift enhancement

drag reduction

and noise control design of aircraft high-lift devices.

关键词

Keywords

references

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