Research on scale effect in subscale flight testing of civil aircraft based on CFD method

CHEN Kai; WU Dawei; SUN Yuchen; CHEN Shi; CHENG Pan; MAO Kun

doi:10.7638/kqdlxxb-2023.0218

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Research on scale effect in subscale flight testing of civil aircraft based on CFD method

更新时间：2026-07-27

- Research on scale effect in subscale flight testing of civil aircraft based on CFD method
- Vol. 42, Issue 8, Pages: 77-83(2024)
- 作者机构：
  
  上海飞机设计研究院,上海,201210
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0218
  CLC： V217+.1
- Published：2024
- 稿件说明：
移动端阅览
陈恺, 吴大卫, 孙宇辰, 等. 基于CFD方法的民用飞机缩比飞行试验尺度效应研究[J]. 空气动力学学报, 2024, 42(8): 77−83.

CHEN Kai, WU Dawei, SUN Yuchen, et al. Research on scale effect in subscale flight testing of civil aircraft based on CFD method[J]. 2024, 42(8): 77-83.
陈恺, 吴大卫, 孙宇辰, 等. 基于CFD方法的民用飞机缩比飞行试验尺度效应研究[J]. 空气动力学学报, 2024, 42(8): 77−83. DOI： 10.7638/kqdlxxb-2023.0218

CHEN Kai, WU Dawei, SUN Yuchen, et al. Research on scale effect in subscale flight testing of civil aircraft based on CFD method[J]. 2024, 42(8): 77-83. DOI： 10.7638/kqdlxxb-2023.0218.

摘要

缩比飞行试验在民用飞机的研制过程中日益受到重视，其尺度效应影响评估是设计缩比飞行试验工况的基础，也是确认飞行数据适用性的关键。基于几何和动力学相似准则，针对某民用飞机及其缩比验证机设计分析工况组，采用计算流体力学方法研究相似准则参数（马赫数

、雷诺数

、弗劳德数

）对气动载荷、典型气动导数及弹性变形的影响。研究结果表明，在动力学相似时，验证机与原型机间的气动特性差异主要来源于马赫数，雷诺数影响较小；当原型机以中低马赫数（

0.5）飞行时，此时马赫数压缩效应不明显，验证机与原型机具有近似的展向与弦向载荷分布特征，典型稳定导数及操纵导数差异约10%，在控制律设计鲁棒性范围内；进一步保持质量与刚度分布相似时，机翼翼尖扭转变形差异不超过0.5°，挠度差异不超过0.5%，在工程上属于可接受的范围。

Abstract

Scale effect evaluation is the foundation for designing scaled flight test conditions and the key to validate the flight data in the development of civil aircraft. Based on geometric similarity and dynamic similarity criteria

the present paper utilizes computational fluid dynamics to analyze the effects of similarity criteria parameters such as Mach number

Reynolds number

and Froude number on aerodynamic loads

aerodynamic coefficients

and elastic deformation for a civil aircraft and its scaled model. Results demonstrate that when the dynamic similarity is satisfied

he differences between the prototype and its scaled model come from the Mach number whereas the effects of the Reynolds number is relatively small. When the prototype is flying at low Mach numbers (

0.5)

the compression effects are not significant

and the scaled prototype exhibits similar spanwise and chordwise load distribution characteristics

with typical stability coefficients and control coefficients differing by approximately 10%

which is within the robustness range for control law design. Furthermore

when maintaining similar mass and stiffness distributions

the maximum deflection of the wingtip twist does not exceed 0.5°

and the maximum deflection does not exceed 0.5%

which are acceptable for engineering applications.

关键词

Keywords

references

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