Wing profile optimal design method of parallel difference evolutionary algorithm based on open computing language (Open CL)

A differential evolution algorithm and optimization design technology, applied in computing, special data processing applications, instruments, etc., can solve the problem of reducing the complexity of genetic operations, etc., to reduce computational complexity, improve airfoil design efficiency, and good portability Effect

Inactive Publication Date: 2012-11-14
BEIHANG UNIV
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Problems solved by technology

For simple mutation operations and one-to-one competitive survival strategies, the differential evolution...

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  • Wing profile optimal design method of parallel difference evolutionary algorithm based on open computing language (Open CL)
  • Wing profile optimal design method of parallel difference evolutionary algorithm based on open computing language (Open CL)
  • Wing profile optimal design method of parallel difference evolutionary algorithm based on open computing language (Open CL)

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Embodiment Construction

[0035] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0036] The geometric shape of the airfoil can be expressed by polynomial fitting or analytical function, and the most commonly used airfoil expression method—analytic function linear superposition method is adopted in the present invention. The analytic function linear superposition method expresses the airfoil shape through the linear superposition of the reference airfoil and the shape function. The shape of the airfoil is defined by the reference airfoil, the shape function and the coefficients of the shape function:

[0037] y ( x ) = y 0 ( x ) + Σ k = 1 N c k ...

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Abstract

The invention provides a wing profile optimal design method of a parallel difference evolutionary algorithm based on open computing language (Open CL). The wing profile optimal design method is used for wing profile design. A standard wing profile function and a profile function are selected, the profile function serves as a design variable, an optimization objective function is determined, steps of the difference evolutionary algorithm are divided into different stages according to processed data, and all stages are packaged in different cores for operating based on Open CL. In population updating, mutation operators are used for generating test vectors and crossover operators are used for generating descendants; individuals in a population are restored to the wing profile shape and tested whether to meet geometric constraint; computational fluid dynamics (CFD) analysis is used for obtaining fitness of the individuals and seeking the optimum individual, and whether the optimum individual meets performance constraint is tested; and finally iteration is finished and the optimum result is copied back into a host internal storage. The wing profile optimal design method achieves parallel processing of a wing profile design process, performs sufficient search in effective space, shortens design period, achieves cross-platform wing profile optimal design, and improves design efficiency.

Description

technical field [0001] The invention relates to the technical field of wing airfoil design and the technical field of computer simulation and optimization, in particular to an airfoil optimal design method based on the parallel differential evolution algorithm of OpenCL (Open Computing Language, Open Computing Language). Background technique [0002] Airfoil selection and design is an important work that must be carried out before aircraft design. D.P.Raymer pointed out: "In many respects, the airfoil is the heart of the aircraft." This is because the wing is the main component of the aircraft to generate lift and drag , and the airfoil that makes up the wing has a great influence on the performance of the aircraft. Airfoil affects cruise speed, takeoff and landing performance, stall speed, handling performance (especially near stall) and aerodynamic efficiency in all phases of flight. Designing airfoils with excellent aerodynamic properties such as high lift and low drag i...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 李妮苏泽亚龚光红田超
Owner BEIHANG UNIV
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