摘要
以超临界翼型DFVLR R-4翼型为基本翼型,在前缘30%弦长处,对翼型进行正向(向下)偏转1°、2°和负向(向上)偏转1°、2°,得到4种变弯度翼型并进行跨声速下气动力数值分析。结果表明:在跨声速中,翼型正向偏转阻力发散特性得到改善,负向偏转阻力发散特性变差;在相同来流马赫数下,翼型正偏转升力系数减小,负向偏转,升力系数增大;翼型正向偏转时,失速迎角特性得到改善。综合分析得出,跨声速能够较好地运用前缘可变弯度翼型。
Taking the supercritical airfoil DFVLR R-4 airfoil as the basic airfoil,in front of 30% chord,we had four variable camber airfoils of the positive airfoil deflection1°,2°（down） and negative（up） four1°,2° deflection,and had numerical analysis. Aerodynamics the results showed that： in the transonic airfoil in transonic flow,positive deflection drag divergence characteristics were improved,and the negative deflection drag divergence characteristics of variation became worse; And in the same flow flow Maher number,it reduces the positive deflection airfoil lift coefficient,and has negative deflection,and the lift coefficient increased; When it has airfoil positive deflection,stall characteristics have been improved. The leading edge of the variable camber airfoils can be used to transonic.
作者
马贵春
林义彪
王冠宇
赵垒
MA Guichun;LIN Yibiao;WANG Guanyu;ZHAO Lei(College of Meehatronie Engineering, North University of China, Taiyuan 030051, China)
出处
《兵器装备工程学报》
CAS
北大核心
2018年第4期1-5,共5页
Journal of Ordnance Equipment Engineering
关键词
超临界翼型
前缘可变弯度
跨声速
阻力发散特性
升阻比
失速迎角
percritical airfoil
fi＇ont variable camber
transonic
drag divergence characteristics
lift drag ratio
stall angle
