某层流验证机中央翼段高速巡航气动性能优化设计

唐松祥; 李杰; 张恒; 牛笑天

doi:10.7527/S1000-6893.2022.26766

航空学报 >

2022 , Vol. 43 >Issue 11: 526766 - 526766

DOI: https://doi.org/10.7527/S1000-6893.2022.26766

论文

某层流验证机中央翼段高速巡航气动性能优化设计

唐松祥 ,
李杰 ,
张恒 ,
牛笑天

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西北工业大学航空学院, 西安 710072

收稿日期: 2021-12-07

修回日期: 2021-12-11

网络出版日期: 2022-11-28

基金资助

国家自然科学基金（11972304）

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Aerodynamic performance optimization design of middle wing section of a special laminar unmanned flight in high-speed cruise

TANG Songxiang ,
LI Jie ,
ZHANG Heng ,
NIU Xiaotian

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School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2021-12-07

Revised date: 2021-12-11

Online published: 2022-11-28

Supported by

National Natural Science Foundation of China (11972304)

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摘要

针对某特殊布局层流机翼验证机，开展高速巡航状态下中央翼段气动性能的优化设计研究。以γ-Re_θ转捩预测方法作为计算分析手段，对中央翼段翼型剖面进行改进设计以提升其升阻特性，并在此基础上对中央翼段前后位置进行调整，探究翼段位置变化后表面转捩位置的变化情况，为改善全机巡航力矩特性提供一定依据。对原始层流翼型和某传统翼型计算和风洞试验结果进行对比，验证了所采用数值计算方法和模型的适用性。针对原始层流翼型，通过提升其同一迎角下的升力系数来降低巡航迎角，增加其巡航状态表面层流区长度，使其拥有更好的层流特性。最后，针对中央翼段平移构型气动力系数开展计算研究，对比分析了不同平移位置中央翼段对层流验证机气动参数的影响，结果表明，不同平移构型在同样的计算状态下，中央翼段表面层流区长度变化不大，构型的变化对其层流特性的影响相对较小，有利于后续从中央翼段平移的角度对全机力矩特性进行优化。

关键词： 中央翼段; γ-Re_θ转捩模型; 气动性能; 翼型优化; 层流特性

本文引用格式

唐松祥 , 李杰 , 张恒 , 牛笑天 . 某层流验证机中央翼段高速巡航气动性能优化设计[J]. 航空学报, 2022 , 43(11) : 526766 -526766 . DOI: 10.7527/S1000-6893.2022.26766

Abstract

In this paper, the aerodynamic parameters of the middle wing of a special configuration laminar flow in high speed cruise are optimized. The lift and drag are optimized by means of airfoil modification of the middle wing section based on the γ-Re_θ transition model. Effects of the middle wing position on transition are researched to provide a basis for improving the cruising torque characteristics of the flight. The applicability of the calculation model is illustrated by comparing the calculation and wind tunnel test results of the original laminar flow airfoil and a traditional airfoil. The original laminar airfoil is modified to improve the lift coefficient at the same attack angle and reduce the cruise attack angle, so as to enlarge the laminar region and improve the laminar characteristics at the condition of high speed cruise. Finally, the aerodynamic calculations of different translation configurations of the middle wing section are conducted. The results show that the laminar region changes little along with the wing section translated. A comparison of the lift and drag coefficients of different translational configurations at the same attack angle shows little effect of configuration on lift and drag, which may provide some insights for torque optimization of the entire aircraft by translating the middle wing section in the future study.

Key words： middle wing section; γ-Re_θ transition model; aerodynamics; airfoil optimization; laminar flow characteristic

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