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An openmp parallel perturbation domain update method for aircraft aerodynamic simulation

A technology of aerodynamic characteristics and aircraft, applied in special data processing applications, geometric CAD, design optimization/simulation, etc., can solve problems such as loss of computational efficiency, and achieve the effect of avoiding invalid calculations

Active Publication Date: 2021-11-09
BEIHANG UNIV
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Problems solved by technology

[0005] The purpose of the present invention is to overcome the deficiencies in the prior art, to provide an OpenMP parallel disturbance domain update method for aircraft aerodynamic characteristics simulation, which can deal with the problems of a large number of invalid calculations in the existing parallel numerical simulation method when simulating aircraft aerodynamic characteristics, and It can solve the problem of possible loss of computational efficiency when the existing disturbance area update method is carried out in large-scale parallelism, and can also minimize the workload of inner boundary processing based on the new data structure and loop structure

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  • An openmp parallel perturbation domain update method for aircraft aerodynamic simulation
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  • An openmp parallel perturbation domain update method for aircraft aerodynamic simulation

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Embodiment 1

[0115] Such as figure 1 Shown, the OpenMP parallel perturbation domain update technology of aircraft aerodynamic characteristic simulation of the present invention specifically comprises the following steps:

[0116] S1: Data read in:

[0117] Allocate storage space for grid coordinates and block information, and read in data such as multi-block structured grids, boundary conditions, and calculation settings of the aircraft flow field.

[0118] S2: Static region decomposition:

[0119] Merge the read-in multi-block structured grid to the minimum number of blocks; divide the grid into grid sub-blocks and evenly distribute them to threads according to the number of cells in the grid. figure 2 Taking the two-dimensional grid as an example to illustrate the grid processing method of the present invention, in the figure a , b Indicates the number of cells along the grid direction. figure 2 a) shows the multi-block structure grid read in, including 3 grid blocks and 2 inner b...

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Abstract

An OpenMP parallel disturbance domain update method for aircraft aerodynamic characteristics simulation, including data reading, static domain decomposition, establishment of dynamic calculation domain, dynamic domain decomposition, storage space allocation, boundary condition processing, residual error estimation, time integration, intra-block increment Large convective dynamic domain, shrinking dynamic calculation domain within a block, increasing viscous dynamic domain within a block, reducing viscous dynamic domain within a block, increasing dynamic calculation domain between blocks, judging whether the solution has reached the convergence condition, and outputting results can be implemented for Existing parallel numerical simulation methods have a large number of invalid calculations when simulating the aerodynamic characteristics of aircraft, and the existing disturbance region update methods may lose computational efficiency when large-scale parallelism is carried out.

Description

technical field [0001] The invention relates to the field of computational fluid dynamics, in particular to an OpenMP parallel disturbance domain update method for aircraft aerodynamic characteristic simulation. Background technique [0002] Computational fluid dynamics numerical simulation has changed the design process of contemporary aircraft and has become an indispensable key technology in the design of various advanced aircraft. Through the efficient integration of existing technology and new technology, the calculation efficiency of numerical simulation is continuously improved, which has important engineering application value for improving the iteration efficiency of aircraft design and shortening the development cycle. [0003] Parallel technology is one of the acceleration technologies that must be used in the simulation of aircraft aerodynamic characteristics. The acceleration principle of parallel technology is mainly to decompose the computing task into multip...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/23G06F30/28
CPCG06F30/23G06F30/15G06F30/28Y02T90/00
Inventor 蒋崇文胡姝瑶高振勋李椿萱
Owner BEIHANG UNIV
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