鸭式布局飞行器的翼体摇滚特性风洞试验
收稿日期: 2015-12-31
修回日期: 2016-01-11
网络出版日期: 2016-02-22
基金资助
江苏高校优势学科建设工程资助项目
Wind tunnel test for wing-body rock of canard-configuration aircraft
Received date: 2015-12-31
Revised date: 2016-01-11
Online published: 2016-02-22
Supported by
Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions
魏德宸 , 史志伟 , 耿玺 , 刘超 , 昂海松 . 鸭式布局飞行器的翼体摇滚特性风洞试验[J]. 航空学报, 2016 , 37(10) : 3003 -3010 . DOI: 10.7527/S1000-6893.2016.0042
In order to study wing-body rock of the canard-configuration aircraft, different methods including free rolling motion, applying disturbance to free rolling motion, static force balance test, dynamic derivative test and smoke wire technique are used for the model which has canard wing, chine forebody, strake wings, main wings and a vertical fin in the wind tunnel. The roll angle time history is obtained by free rolling motion and disturbed motion, and then non-limit cycle motion is verified by static force balance test and dynamic derivative test. The results show that rolling motions of the canard-configuration aircraft model have several different central angles in the same side, and one center can jump to the other at the critical pitch angles. Finally, the basic flow field distribution of the canard-configuration aircraft model is described by flow visualization technique. The vortex system interaction mechanism and cause of wing-body rock of model are briefly analyzed at 0°rock angle.
Key words： canard wing; wing-body rock; non-limit cycle; dynamic derivative; flow visualization
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