特殊布局高亚声速层流无人验证机基本翼气动力协调设计

李杰; 张恒; 杨钊

doi:10.7527/S1000-6893.2022.26786

航空学报 >

2022 , Vol. 43 >Issue 11: 526786 - 526786

DOI: https://doi.org/10.7527/S1000-6893.2022.26786

论文

特殊布局高亚声速层流无人验证机基本翼气动力协调设计

李杰 ,
张恒 ,
杨钊

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1. 西北工业大学航空学院, 西安 710072;
2. 清华大学航天航空学院, 北京 100084

收稿日期: 2021-12-08

修回日期: 2022-01-05

网络出版日期: 2022-01-26

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Trade-off aerodynamic design of basic wing for demonstrator UAVs with special layout for high-subsonic laminar flow verification

LI Jie ,
ZHANG Heng ,
YANG Zhao

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1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. School of Aerospace Engineering, Tsinghua University, Beijing 100084, China

Received date: 2021-12-08

Revised date: 2022-01-05

Online published: 2022-01-26

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摘要

高亚声速层流无人验证机首创性地采用内侧等直试验段与外侧后掠基本翼相结合的特殊气动布局形式，基本翼与试验段在整体飞行特性层面的协调匹配及基本翼自身的高低速特性协调匹配是气动力设计的出发点。根据典型飞行试验任务对高速巡航效率和低速失速特性的设计需求，针对性剖析了高低速气动特性的主控因素与设计原理。结合全速势-附面层修正方法设计、数值模拟校核的思路开展了兼顾巡航点激波/环量特性及低速分离顺序的基本翼气动力协调设计研究，形成了工程适用的设计方案。数值模拟和风洞试验综合评估结果表明：设计方案实现了大尺寸翼吊短舱影响下的巡航点无激波压力分布稳健性设计，在高亚声速验证工况气动特性良好的前提下，有效保证了低速临界迎角状态翼面分离梯次合理、升力/力矩可用，实现了基本翼与飞行试验验证需求及高低速气动特性的双重协调匹配。

关键词： 层流验证; 无人机; 内外翼协调; 高低速协调; 巡航特性; 失速特性

本文引用格式

李杰 , 张恒 , 杨钊 . 特殊布局高亚声速层流无人验证机基本翼气动力协调设计[J]. 航空学报, 2022 , 43(11) : 526786 -526786 . DOI: 10.7527/S1000-6893.2022.26786

Abstract

The pioneering demonstrator UAV for high-subsonic laminar flow verification adopts a special aerodynamic layout combining the inner straight section and the outer swept wing. The aerodynamic design starts with the coordination of the overall flight performance between the basic wing and the test section as well as the coordination of the high-low speed performance of the basic wing itself. According to the requirements of flight tests for high-speed flight efficiency and low-speed stall performance of the basic wing, the main control factors and design principles of high-low speed performance are analyzed, and the integrated aerodynamic design of the performance of shock waves and circulation at the cruise point as well as the separation pattern at a low-speed are conducted based on the velocity potential method with boundary-layer correction for design and numerical simulation for verification. A practical aerodynamic design of the basic wing is then created. The results of numerical simulation and the experiment prove the robustness of the design of shock-free pressure distribution under the influence of large scale nacelles. The efficient performance under the high-subsonic condition is achieved while the proper position and development order of separation as well as available lift and moment are ensured at a low speed for the basic wing at the critical angle of attack. The dual coordination of the basic wing for the demonstration requirements at the cruise point and the high-low speed performance are therefore acquired.

Key words： laminar demonstrator; unmanned aerial vehicles (UAV); trade-off design of inner and outer wings; trade-off design of high-low speed performance; cruise performance; aerodynamic stalling

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