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An Airfoil Optimization Method Based on Genetic Algorithm and Numerical Simulation

An optimization method and numerical simulation technology, applied in the field of airfoil optimization, can solve problems such as limiting the optimization space of the airfoil profile and limiting the optimal design of the airfoil, so as to reduce the amount of calculation, improve the optimization efficiency, and expand the scope of optimization. Effect

Active Publication Date: 2022-08-02
HUAZHONG UNIV OF SCI & TECH
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Problems solved by technology

These all limit the optimization space of the airfoil line to a certain extent, and then limit the optimal design of the airfoil.

Method used

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  • An Airfoil Optimization Method Based on Genetic Algorithm and Numerical Simulation
  • An Airfoil Optimization Method Based on Genetic Algorithm and Numerical Simulation
  • An Airfoil Optimization Method Based on Genetic Algorithm and Numerical Simulation

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[0029] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as there is no conflict with each other.

[0030] see figure 1 , the present invention provides an airfoil optimization method based on genetic algorithm and numerical simulation, and the method includes steps S1-S4.

[0031] S1, using high-order Bezier curves to describe parametrically the profiles of the upper and lower surfaces of the airfoil, so that the profiles of the upper and lower surfaces of the airfoil are controlled by a plurali...

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Abstract

The invention belongs to the technical field of airfoil optimization, and discloses an airfoil optimization method based on genetic algorithm and numerical simulation. Carry out parameterized description; obtain multiple airfoils and corresponding angles of attack; obtain the objective function values ​​of multiple airfoils at the corresponding angles of attack through numerical simulation; use genetic algorithm to sort the objective function values, and select the objective function values ​​that satisfy the predictions. Set the airfoil and the angle of attack corresponding to the objective function value of the rule as the target airfoil and the target angle of attack, select and cross and / or mutate the coordinates of the control point corresponding to the target airfoil and the target angle of attack to obtain the optimal airfoil set , and repeat the numerical simulation and genetic algorithm processing for the optimized airfoil set until the objective function value reaches the optimization termination condition. Combined with genetic algorithm and numerical simulation technology, this method can obtain the airfoil and angle of attack with the optimal objective function value in a larger optimization range.

Description

technical field [0001] The invention belongs to the technical field of airfoil optimization, and more particularly relates to an airfoil optimization method based on genetic algorithm and numerical simulation. Background technique [0002] Airfoil is one of the important geometric characteristics of structural components such as blades and wings. It is used in aircrafts in the aerospace field, fans, pumps and wind turbines in the energy field, and civil equipment such as air conditioners and ventilation fans. With the continuous development of society and the continuous improvement of human needs, higher requirements are placed on the performance of airfoils. [0003] For the optimization of airfoils, the more conventional optimization method at present is to select an initial airfoil first, use the airfoil profile parameterization method to describe it parametrically, select relevant parameters from it as optimization variables, and add them to Constraints, determine the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/20G06N3/12
CPCG06F30/15G06F30/20G06N3/126
Inventor 王嘉冰杨昆王超尘周博文曾琳琅
Owner HUAZHONG UNIV OF SCI & TECH
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