自然层流减阻验证方法及验证翼段布局设计

周桢尧; 吕飞; 周斌; 杨钊

doi:10.7527/S1000-6893.2022.26751

航空学报 >

2022 , Vol. 43 >Issue 11: 526751 - 526751

DOI: https://doi.org/10.7527/S1000-6893.2022.26751

论文

自然层流减阻验证方法及验证翼段布局设计

周桢尧 ,
吕飞 ,
周斌 ,
杨钊

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1. 航空工业第一飞机设计研究院, 西安 710089;
2. 陕西飞机工业有限责任公司, 汉中 723213;
3. 西北工业大学航空学院, 西安 710072

收稿日期: 2021-12-06

修回日期: 2022-01-13

网络出版日期: 2022-02-28

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Verification method for natural laminar flow drag reduction and layout design of test section

ZHOU Zhenyao ,
LYU Fei ,
ZHOU Bin ,
YANG Zhao

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1. AVIC The First Aircraft Institute, Xi'an 710089, China;
2. China Aviation Industry Shanxi Aircraft Industry (Group) Co. Ltd, Hanzhong 723213, China;
3. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2021-12-06

Revised date: 2022-01-13

Online published: 2022-02-28

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摘要

飞行试验是评估层流设计技术效能的有效手段，验证翼段布局参数是无人验证机气动力设计的出发点。澄清了"相同设计升力系数法"的工程实用价值，创新性设计了涵盖数值模拟、风洞试验、飞行试验的自然层流翼型减阻效果综合验证试验体系，在此基础上完善了1 t级双机身布局无人验证机初步方案。基于CFD手段详细分析了验证翼段弦长、展长、安装位置、安装角等关键布局参数对飞行试验效能及验证机本体气动特性的影响。风洞试验结果验证表明：验证翼段布局参数选择合理，纵向静稳定性适中，能够保持大范围稳定二维区域，满足飞行试验验证要求。

关键词： 自然层流; 气动布局设计; 层流翼型; 飞行试验; 风洞试验

本文引用格式

周桢尧 , 吕飞 , 周斌 , 杨钊 . 自然层流减阻验证方法及验证翼段布局设计[J]. 航空学报, 2022 , 43(11) : 526751 -526751 . DOI: 10.7527/S1000-6893.2022.26751

Abstract

Flight tests are effective in efficiency evaluation for the laminar flow design technology, while the layout parameters of the test wing section are the starting point for the aerodynamic design of unmanned demonstrators. This paper confirms the engineering value of "the same design lift coefficient method", and innovatively designs a comprehensive verification test system for drag reduction effect of natural laminar airfoils, including numerical simulation, wind tunnel tests and flight tests. On this basis, the preliminary scheme of the unmanned verification aircraft with 1 t twin-fuselage configuration is improved. The influence of crucial layout parameters such as chord length, span length, installation position and installation angle on the performance of flight tests and the aerodynamic characteristics of the test wing section are analyzed based on CFD. The wind tunnel test results show that the layout parameters of the demonstrator test wing section are reasonable, the longitudinal static stability of the demonstrator is moderate, and the test section can maintain a large range of stable two-dimensional flow area, thereby satisfying the flight test verification requirements.

Key words： natural laminar flow; aerodynamic layout design; laminar airfoil; flight test; wind tunnel test

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