摘要
基于改进升力线方法，编制了螺桨升力线方法计算程序，并以此为基础，在桨尖外引入一层虚网格和虚控制点；利用升力线理论中导出的附着涡和自由涡的积分公式，发展了一种螺旋桨气动性能计算的升力面方法，该方法具有简洁、方便、实用等特点。用本文发展的升力线和升力面方法对多个螺旋桨算例进行了计算，计算结果与实验结果符合良好。
t is inappropriate to applied classical propeller theories to predicte the aerodynamic performance of an advanced turboprop. Sullivan has presented attractive results by using the curved lifting line method. His method has been developed to the lifting surface method (vortex-lattice method), but the calculation is more complicated.This paper presents a lifting surface method which is based on Sullivan's curved lifting line method. The virtual grid and the virtual control points at the propeller tip are introduced. The integral expressions, which is used in lifting line method to calculate the induced velocities generated by the bound vortices and the belieal trailing vortices, can be directely applied to the lifting surface method. Thismakes the lifting surface method simple and convenient. The lifting line and lifting surface code which is developed by authors are applied to three NACA propeller.The comparision of numerical results with experiment data is presented. The numerical results of the lifting surface method are in good agreement with the experimental data. The present method is very effective for practical engineering applications.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1994年第5期41-47,共7页
Journal of Propulsion Technology
关键词
螺旋桨
气动力
计算
升力线理论
涡桨发动机
Aircraft propeller, Aerodynamic computation, Lifting line theory,Lifting surface theory
