A direct numerical simulation method for compressible turbulent flow based on compact high-resolution hybrid scheme
A high-resolution, numerical simulation technology, applied in the direction of complex mathematical operations, electrical digital data processing, special data processing applications, etc., can solve problems such as large numerical dissipation and difficulty in compressible turbulent numerical simulation, and achieve small numerical consumption Dispersion, improved resolution, and good spectral characteristics
Inactive Publication Date: 2019-05-31
BEIHANG UNIV
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Problems solved by technology
However, the numerical dissipation of the nonlinear shock wave capture format is large, and the spectral characteristics are far inferior to the linear format, so it is difficult to meet the requirements of direct numerical simulation of compressible turbulent flow.
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Embodiment 1
[0079] Example 1: Shock wave and density wave interference problem
[0080] This example is a basic example to test the performance of numerical simulation of compressible turbulent flow in computational format. The calculation area is [-5,5]×[0,0.2]×[0,0.2], and the number of grid cells is given as 200×4×4, such as Figure 4 . Given initial conditions:
[0081]
[0082] Appropriate boundary conditions are assigned to each boundary, such as Figure 5 . Calculate according to the above steps, the termination time t end = 1.8.
[0083] Image 6 The distribution curve of the density along the x-axis is the simulation result of this embodiment. Image 6 It can be seen that the present invention clearly captures the shock wave in the flow field (x<0.5 region), indicating that the present invention can capture the strong discontinuity in the flow field stably and with high precision;
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The invention relates to a compressible turbulence direct numerical simulation method based on a compact type high resolution hybrid format. Aiming at the characteristics that compressible turbulent not only needs a higher flow field resolution to capture a small-scale flow structure, but also needs to stably capture shock waves, the method utilizes a mixed function based on local flow field variables to mix two different numerical formats, and uses a high-resolution linear upwind compact format in a smooth flow area and uses a compact type nonlinear shock wave capturing format in an interruption area, thus reaching the requirement of compressible turbulence direct numerical simulation. Compared with the existing high-order formats used for compressible turbulence direct numerical simulation, the compressible turbulence direct numerical simulation method based on the compact type high resolution hybrid format uses the hybrid format which also has higher resolution near interruption, thus further reducing numerical dissipation and chromatic dispersion near the interruption, and reducing the influence on whole flow field calculation caused by numerical dissipation introduced by capturing the shock waves to a greatest extent. After the hybrid format is used, computational accuracy is effectively improved, and computational expense is reduced.
Description
technical field [0001] The invention relates to the technical field of computational fluid dynamics, in particular to a direct numerical simulation method suitable for compressible turbulent flow based on a compact high-resolution hybrid format. Background technique [0002] Turbulence is a flow phenomenon that exists widely in nature. Because of its complex characteristics such as multi-scale, randomness, irregularity, instability, nonlinearity, and eddyness, human beings have not yet understood its mechanism, and it is difficult to develop and evolve it. process to predict. At the same time, turbulence involves many aspects in the industrial field, such as turbulent noise, turbulent drag reduction, etc. Especially in the field of aerospace, the flow in the area where the aircraft is located plays a decisive role in the load distribution of the aircraft, and the prediction of the involved flow structure is crucial to the design of the aircraft. However, due to the faster ...
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IPC IPC(8): G06F17/50G06F17/12
CPCG06F17/12G06F30/20
Inventor 李彦苏于剑阎超
Owner BEIHANG UNIV
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