平板大攻角绕流升力和阻力系数的计算  

Lift and drag coefficients of flow around a flat plate at high attack angles

作　　者：姜海波[1,2] 曹树良[2] 程忠庆[1] 

机构地区：[1]海军工程大学天津校区,天津300450 [2]清华大学,北京100084

出　　处：《应用力学学报》2011年第5期518-520,557,共3页Chinese Journal of Applied Mechanics

摘　　要：二维平板或二维对称薄翼型大攻角绕流升力和阻力系数与攻角之间存在的函数关系一般用数据表格的形式给出。本文根据垂直平板绕流阻力实验数据和对称薄翼型全攻角绕流实验数据,分析得到了平板大攻角绕流总压力及其升力分量和阻力分量系数的近似计算公式。结果表明:平板总压力系数约等于攻角正弦值的2倍;总压力的阻力分量系数约等于攻角正弦值平方的2倍;升力分量系数约为攻角2倍的正弦值。计算结果与两组试验数据具有较好的一致性。The function relationship between the lift and drag coefficients and the attack angles of flow around a flat or a two-dimensional symmetric thin airfoil was expressed in data tabular form generally.In this paper,the approximate formulas of the total pressure and its lift and drag components of incompressible flow around a flat at high attack angles are obtained by using experimental data of flow around airfoils at high attack angles.The results show that the total pressure coefficient at high attack angles is equal to two times of the sine of the attack angle approximately.The results also show that its drag component coefficient at high attack angles is equal to two times of the square of the sine of the attack angle,and its lift component coefficient is equal to the sine of two times of the attack angle approximately.The comparison shows good agreement between the computational and experimental data at high attack angles.

关 键 词：平板 大攻角绕流 升力系数 阻力系数 总压力 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]