实验流体力学2011，Vol.25Issue(6)：6-12,7.
80°/65°双三角翼模型大迎角气动特性风洞实验研究
Experimental research on the high angle of attack aerodynamic characteristics of an 80°/65° double-delta wing
孙海生 1姜裕标 2刘志涛 2史喆羽2
作者信息
- 1. 西北工业大学航空学院,西安710072
- 2. 中国空气动力研究与发展中心低速所,四川绵阳621000
- 折叠
摘要
Abstract
The aerodynamic characteristics,pressure distribution and flowfield evolution of an 80°/65° double-delta wing model have been studied in φ3.2m low speed wind tunnel at CARDC by means of force measurement,pressure measurement and PIV technique.The Reynolds number is 0.49～1.3( × 106)and the range of angle of attack(AoA) is between 0° and 60°.The study indicates that the results obtained from different types of tests have good correlation.The lift coefficient reaches maximum at 30° AoA,changes slightly between 30°～37° AoA,then drops rapidly as AoA increases.When AoA exceeds 30°,the leading edge vortex begins to break down.From 38° to 40° AoA,the suctionpeak disappears gradually and pressure coefficient decreases evidently.After 40° AoA,the suction peak disappears completely and leading edge vortex breaks down totally.关键词
双三角翼/大迎角空气动力学/流动机理/风洞实验/涡破裂Key words
double-delta wing /high angle of attack aerodynamics /flow mechanism /wind tunnel test /vortex breakdown分类
数理科学引用本文复制引用
孙海生,姜裕标,刘志涛,史喆羽..80°/65°双三角翼模型大迎角气动特性风洞实验研究[J].实验流体力学,2011,25(6):6-12,7.
