翼型气动性能改进的实验研究  

EXPERIMENTAL INVESTIGATION OF AIRFOIL AERODYNAMIC CHARATERISTICS IMPROVEMENT

作　　者：刘宝杰[1] 杨晓宁[1] 沈遐龄 高歌 

机构地区：[1]京航空航天大学404教研室,北京100083

出　　处：《工程热物理学报》1999年第1期53-56,共4页Journal of Engineering Thermophysics

基　　金：国防基金

摘　　要：This paper presents the experimental investigations of NACA0012 airfoil aerodynamiccharacteristics improvement by airfoil tail tailoring (30% chord part ) in low speed windtunnel. Experiment Renolds number range is 4.9x 10~5 to 6.5x10^5, and the angle--of--attackrange is -12° to 12°. The comparisons of experimental results show that: tail tailoring canincrease both airfoil lift and lift--to--drag ratio in the positive angle--of--attack range; it candecrease airfoil drag in the negative angle--of--attack range.This paper presents the experimental investigations of NACA0012 airfoil aerodynamiccharacteristics improvement by airfoil tail tailoring (30% chord part ) in low speed windtunnel. Experiment Renolds number range is 4.9x 10~5 to 6.5x10^5, and the angle--of--attackrange is -12° to 12°. The comparisons of experimental results show that: tail tailoring canincrease both airfoil lift and lift--to--drag ratio in the positive angle--of--attack range; it candecrease airfoil drag in the negative angle--of--attack range.

关 键 词：增升 流动控制 几何修形 翼型 气动性能 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]