超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验

张彦军; 段卓毅; 雷武涛; 白俊强; 徐家宽

doi:10.7527/S1000-6893.2018.22429

航空学报 >

2019 , Vol. 40 >Issue 4: 122429 - 122429

DOI: https://doi.org/10.7527/S1000-6893.2018.22429

流体力学与飞行力学

超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验

张彦军 ,
段卓毅 ,
雷武涛 ,
白俊强 ,
徐家宽

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1. 航空工业第一飞机设计研究院, 西安 710089;
2. 西北工业大学航空学院, 西安 710072

收稿日期: 2018-06-07

修回日期: 2018-06-25

网络出版日期: 2018-08-16

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Design of supercritical natural laminar flow wing and its boundary layer transition wind tunnel test based on TSP technique

ZHANG Yanjun ,
DUAN Zhuoyi ,
LEI Wutao ,
BAI Junqiang ,
XU Jiakuan

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1. AVIC the First Aircraft Institute, Xi'an 710089, China;
2. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2018-06-07

Revised date: 2018-06-25

Online published: 2018-08-16

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摘要

为了实现绿色航空节能减排的目标，层流设计技术成为飞行器设计者的研究热点。对于跨声速客机而言，超临界自然层流机翼设计技术将显著减小飞行阻力，提升气动性能，减少燃油消耗和污染物排放。首先，基于高精度边界层转捩预测技术耦合翼型优化设计系统，实现超临界自然层流翼型设计；经过合理的翼型配置，形成超临界自然层流机翼。转捩数值模拟分析结果表明，超临界自然层流机翼的层流流动特性良好。然后，以比例为1：10.4的试验模型在荷兰高速低湍流度风洞进行边界层转捩风洞试验，使用温度敏感材料涂层（TSP）技术拍照获得机翼表面在不同马赫数、雷诺数和迎角工况下的层流-湍流分布。最后，通过超临界自然层流机翼边界层转捩试验结果，探讨了该类型机翼的转捩特性随来流参数的变化规律，总结了超临界自然层流机翼设计的关键因素。此外，该模型也可用来验证边界层转捩预测技术在超临界、高雷诺数工况下的预测精度。

关键词： 自然层流; 超临界机翼; 高雷诺数; 边界层转捩; 温度敏感材料涂层(TSP); 风洞试验

本文引用格式

张彦军 , 段卓毅 , 雷武涛 , 白俊强 , 徐家宽 . 超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验[J]. 航空学报, 2019 , 40(4) : 122429 -122429 . DOI: 10.7527/S1000-6893.2018.22429

Abstract

To achieve the green aviation goal of energy conservation and emission reduction, laminar flow design technology has become the hot research area for aircraft designers. For transonic airliners, supercritical natural laminar flow wing design technology will significantly reduce the flight drag, improve aerodynamic performance, and decrease fuel consumption and pollutant emissions. Based on the high-precision boundary layer transition prediction technique, the airfoil optimization design system is applied to design the supercritical natural laminar flow airfoils. Then the airfoils are arranged rationally to form the supercritical natural laminar flow wing. Numerical simulations of the supercritical natural laminar flow wing show satisfactory laminar flow characteristics. Then, a model with ratio of 1:10.4 is used to test the boundary layer transition in high speed and low turbulence wind tunnel in Netherland. The Temperature Sensitive Paint (TSP) technique is used to photograph laminar-turbulent area distribution at different Mach numbers, Reynolds numbers and angels of attack. At last, the boundary layer transition characteristics of the supercritical natural laminar flow wing are discussed, and the key factors of the wing design are summarized. In addition, the model can also be used to verify the accuracy of the boundary layer transition prediction technique for supercritical and high Reynolds numbers condition.

Key words： natural laminar flow; supercritical wing; high Reynolds number; boundary layer transition; Temperature Sensitive Paint (TSP); wind tunnel test

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