Design method for propeller blade

Abstract

The invention discloses a design method for a propeller blade. The propeller design is performed by adopting an optimal load distribution curve; and it is concluded that a ratio of local effective power to local consumption power of a blade element has the optimal distribution curve. The propeller design is performed according to the curve, so that relatively high aerodynamic efficiency can be achieved without performing three-dimensional numerical optimization. The design cycle can be shortened and the improvement of the aerodynamic efficiency of the blade can be assisted; and the three-dimensional numerical optimization design does not need to be performed, so that the design cycle is only 1-2 days.

Description

Technical field

[0001] The invention relates to a design method of a propeller for an aircraft, in particular to a design method for the aerodynamic shape of the propeller of a medium and small unmanned aerial vehicle. Background technique

[0002] In the existing propeller design, the initial data (propeller required power, forward speed, forward ratio, blade diameter, number of blades) and other technical indicators are generally determined first, and then the aerodynamic design of the propeller is carried out. Using the two-dimensional element theory (such as the widely used Betz method) combined with the initial data of the propeller to determine the airfoil of each section of the blade and its corresponding torsion angle. Although the two-dimensional design method is relatively simple, the actual propeller is three-dimensional, so it is difficult to achieve the high efficiency due to the two-dimensional design.

[0003] At present, the aerodynamic performance optimization des...

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