Design method for propeller blade

A design method and technology for propellers, which are applied in the fields of calculation, image data processing, special data processing applications, etc., can solve problems such as the inability to effectively determine the overall efficiency of the propeller, and achieve the effect of shortening the design cycle and high aerodynamic efficiency.

Active Publication Date: 2018-01-19
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Studies have shown that observing the blade element thrust distribution and the blade element

Method used

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  • Design method for propeller blade
  • Design method for propeller blade
  • Design method for propeller blade

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0063] This embodiment proposes a design method of the propeller blade with the optimal load distribution. The specific process is:

[0064] Step 1. Determine the overall parameters of the propeller.

[0065] The overall parameters of the propeller determined include:

[0066] The required power is 50kW; the number of blades B=4; the diameter of the blades D=800mm; the flying height H=6000km; the flying speed V=150km / h; the propeller speed n=5500r.p.m.

[0067] Step 2. Choose the airfoil

[0068] According to the propeller's rotation speed, diameter and flight speed, according to the traditional Reynolds number, Mach number limit conditions and the best working point of the airfoil, determine the airfoil used in each section of the propeller. The propeller airfoil selected in this embodiment is an ARA-D airfoil.

[0069] Step 3. Determine the local thrust dT.

[0070] Determine the local thrust dT of the leaf element according to the local efficiency of leaf element.

[0071] The local ef...

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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...

Claims

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Application Information

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IPC IPC(8): G06F17/50G06T17/00
CPCY02T90/00
Inventor 高远高永卫
Owner NORTHWESTERN POLYTECHNICAL UNIV
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