高速前飞时旋翼气动载荷计算

ROTOR AIRLOAD CALCULATION IN HIGH SPEED FLIGHT

针对大速度前飞的特点,我们研制了一套计算大速度前飞旋翼气动载荷的方法和软件,算例计算表明计算值和试验值有较好的吻合度,它不仅在桨叶内段吻合得较好,而且在桨尖这种大载荷区域也是如此;不仅对前进比μ=0.3以下状态符合得较好,而且对μ=0.4,0.45这种高速状态也是如此。这说明本计算方法与软件对大速度前飞旋翼气动载荷计算达到了一定的精度,基本上能满足工程设计的需要。

An improved roter airloads calculation method in high speed flight is developed, and applied to airloads data from flight tests and wind tunnel tests. The method is based on Weissinger's lifting-surface theory ( i. e. second order lifting-line theory) / rigid wake geometry/ elastic flap mode-elastic torsion correction. The method includes acompiessible flow correction, an unsteady aerodynamics forces correct, a radial flow correction, an empirical dynamic stall correction and a backword flow passage correction. The correlation between calculated and easured airloads is good for flight conditions when not only μ≤0.3 but μ=0.4 , 0.45 .