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Method for calculating aerodynamic load of winglet blade with trailing edge in dynamic stall state

A dynamic stall and aerodynamic load technology, applied in the field of helicopters, can solve problems such as the lack of aerodynamic load models, and achieve the effect of convenient calculation and high precision

Inactive Publication Date: 2019-12-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, there is still a lack of accurate and efficient aerodynamic load models for calculating the aerodynamic loads of blades with trailing edge winglets in dynamic stall conditions

Method used

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  • Method for calculating aerodynamic load of winglet blade with trailing edge in dynamic stall state
  • Method for calculating aerodynamic load of winglet blade with trailing edge in dynamic stall state
  • Method for calculating aerodynamic load of winglet blade with trailing edge in dynamic stall state

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Embodiment Construction

[0033] Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:

[0034] This invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.

[0035] The implementation process of the present invention is as figure 1 shown.

[0036] Step 1. Calculating the generalized aerodynamic loads considering the dynamic stall of the section of the blade with trailing edge winglet;

[0037] Generalized aerodynamic load L n And the amount of attachment cycle Γ can be expressed as:

[0038]

[0039]

[0040] In the formula, [M], [C], [K], [G] represent mass matrix, damping matrix, stiffness matrix and Greenberg matrix respectivel...

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Abstract

The invention discloses a method for calculating aerodynamic load of a winglet blade with a trailing edge in a dynamic stall state. The method comprises the following steps: firstly, calculating induction speed and generalized aerodynamic load considering dynamic stall of a section of the winglet blade with the trailing edge; secondly, establishing a dynamic stall additional aerodynamic load differential equation; then, determining the static loss of the aerodynamic load of the blade section of the winglet with the trailing edge, and establishing an improved dynamic stall additional aerodynamic load model of the blade section of the winglet with the trailing edge; and finally, calculating and correcting the total aerodynamic load of the section of the winglet blade with the trailing edge in the dynamic stall state. The invention provides a high-precision calculation and analysis method for calculating the aerodynamic load of the winglet blade with the trailing edge in a dynamic stall state, and overcomes the defects of low precision, excessive unknown state quantity, complex calculation and the like of the existing method.

Description

technical field [0001] The invention relates to the technical field of helicopters, in particular to a method for calculating the aerodynamic load of a blade with a trailing edge winglet in a dynamic stall state. Background technique [0002] The deflection motion of the winglet at the trailing edge of the helicopter rotor blade has significant effects on the rotor blade to increase lift, improve performance, control vibration and delay the occurrence of dynamic stall. Dynamic stall is an aerodynamic phenomenon in which the dynamic rotation of the airfoil at a high angle of attack causes the airflow on the upper surface of the airfoil to separate and form a turbulent vortex, which moves from the leading edge to the trailing edge and falls off at the trailing edge. With the deflection movement of the airfoil, the phenomenon of excessive lift and torque will appear, and the aerodynamic load will also present a hysteresis curve or a figure-eight curve. Under high-speed and hig...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 尚丽娜夏品奇
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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