关键词: 航空螺旋桨;气动力计算;升力线理论;升力面理论

Abstract: 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.

Key words: Aircraft propeller;Aerodynamic computation;Lifting line theory;Lifting surface theory