小展弦比飞翼标模纵航向气动特性低速实验研究

吴军飞; 秦永明; 黄湛; 魏忠武; 贾毅

doi:10.7638/kqdlxxb-2015.0093

小展弦比飞翼标模纵航向气动特性低速实验研究

中国航天空气动力技术研究院, 北京 100074

详细信息

作者简介:
吴军飞(1984-),工程师,主要从事实验空气动力学研究.E-mail:wujunfei2002@163.com

中图分类号: V211.7
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- 文章访问数: 240
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- PDF下载量: 628
出版历程
- 收稿日期: 2015-07-20
- 修回日期: 2015-10-22
- 网络出版日期: 2021-01-07
- 刊出日期: 2016-01-24

Low speed experiment on longitudinal and lateral aerodynamic characteristics of the low aspect ratio flying wing calibration model

The China Academy of Aerospace Aerodynamics, Beijing 100074, China

摘要

摘要: 对小展弦比飞翼气动布局外形,通过常规测力风洞实验方法得到其纵向气动特性和偏航控制特性,在分析其气动特性后,选取典型的状态采用PIV实验方法对其流动机理进行研究,研究表明小展弦比飞翼在较小的迎角下即出现前缘分离涡,随着迎角的增大,前缘分离涡强度增大,且逐渐往机体对称面方向移动,随着迎角进一步增大,分离涡变得不稳定,涡核开始摆动,最终破裂,破裂位置从后缘开始,逐渐前移。对小展弦比飞翼气动布局飞机的控制难点偏航控制进行研究,结果表明该飞翼布局模型在实验迎角范围内偏航方向是静稳定的,在小迎角下具有可操纵性,迎角大于6°后嵌入面处于破裂的前缘涡尾迹之中,操纵性降低。
- 小展弦比 /
- 飞翼 /
- 纵向气动特性 /
- 偏航控制
Abstract: longitudinal and lateral aerodynamic characteristics of the low aspect ratio flying wing calibration model are investigated in a low speed wind tunnel. Normal force measuring experiment is conducted to gain the longitudinal aerodynamic characteristics and yaw control characteristics, and the PIV test is also conducted to investigate the flow mechanism of the low aspect ratio flying wing. The results indicate that the leading-edge separation vortex appears on the wing's spine surface when the attack angle is at 6 degree. The vortex intensity increases and the vortex core shifts to the symmetric plane of flying wing with the increase of attack angle. Increasing the attack angle further, the vortex core becomes unsteady and begins to oscillate, finally break entirely. The broken position shifts from the ending edge to the leading edge. Yaw control characteristics of low aspect ratio flying wing is also studied in this paper. The results indicate that the flying wing is static stabile at the test attack angle. When the attack angle is less than 6 degree, it is controllable in yaw direction. And when attack angle is more than 6 degree, the yaw control ability decreases because the control surface may lays in the wake region of broken leading-edge vortex.
- low aspect ratio /
- flying wing /
- longitudinal aerodynamic characteristics /
- yaw control

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参考文献(15)

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施引文献(12)

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文章访问数: 240
HTML全文浏览量: 10
PDF下载量: 628
被引次数: 12

小展弦比飞翼标模纵航向气动特性低速实验研究

作者简介: 吴军飞(1984-),工程师,主要从事实验空气动力学研究.E-mail:wujunfei2002@163.com

计量

出版历程

Low speed experiment on longitudinal and lateral aerodynamic characteristics of the low aspect ratio flying wing calibration model

期刊类型引用(4)

其他类型引用(8)

计量

出版历程

目录

作者简介:
吴军飞(1984-),工程师,主要从事实验空气动力学研究.E-mail:wujunfei2002@163.com