摘要
为加深学生对薄翼型升力理论相关知识的理解,使抽象的理论直观化,我们设计了低速简易风洞测量薄翼模型升力系数的实验:利用简单的弹簧测力装置测量不同迎角下翼型的升力系数。实验数据表明,给定薄翼模型的升力系数与来流速度无明显关系、和迎角近似线性。多次实验结果表明,该简易风洞实验可用于半定量验证薄翼型升力理论,也可用于研究其他自制翼型的升力系数。
To deepen students＇understanding of thin airfoil lift theory and make the abstract theory intuitive,an experiment of lift coefficient measurement of thin wing in simple wind tunnel is designed.The lift coefficient of airfoil under different angles of attack is measured by a simple spring device.The experiment data shows that the lift coefficients have no obvious relationship with the inflow velocity and are approximately linear to the angle of attack.Several experimental results show that the simple wind tunnel experiment can be used to validate the lift theory of thin airfoil in semi quantitative sense.It can also be used to study the lift coefficients of other airfoils.
作者
何建勋
唐芳
熊畅
王志超
HE Jianxun1, TANG Fang2, XIONG Chang2, WANG Zhichao3(1 School of Energy and Power Engineering, Beihang University, Beijing 100191; 2 School of Physics and Nuclear Energy Engineering, Beihang University, Beijing 100191 3 School of Mathematics and SystemSeience, Beihang University, Beijing 10019)
出处
《物理与工程》
2018年第2期113-117,共5页
Physics and Engineering
关键词
简易风洞
薄翼型理论
升力系数
迎角
simple wind tunnel~ thin airfoil theory~ lift eoefficient~ angle of attack
