面向超声速民机近/中场声爆传播的空间推进高精度数值模拟方法

doi:10.7527/S1000-6893.2025.31935

Abstract

Abstract:

For the numerical simulation of near-/mid-field sonic boom propagation of a supersonic civil aircraft， the conventional Computational Fluid Dynamics （CFD） using a time-marching method is computationally intensive， while the acoustic propagation method based on solving the augmented Burgers equation has difficulty in simulating velocity and density variations of three-dimensional flows. To address these problems， a high-fidelity numerical simulation method of using a space-marching approach is proposed， and an in-house code “SMFlow3D” is developed. The simulation procedure consists of three steps. First， a structured Mach-aligned grid of a conical shape is generated. Second， circumferential distributions of density， velocity， and pressure variables are extracted at one-body length distance from a supersonic aircraft， and are interpolated to the grid nodes as initial conditions. Third， within a finite difference method framework， three-dimensional steady governing equations in a curvilinear coordinate system are solved along the post-Mach cone direction using a third-order Runge-Kutta method. The developed method was applied to simulate the near-/mid-field sonic boom propagation for the JAXA Wing Body （JWB） model， which was proposed in the 2nd Sonic Boom Prediction Workshop. The predicted sonic-boom waveforms are compared with the results obtained from conventional CFD method and acoustic propagation method based on the augmented Burgers equation， validating the accuracy and effectiveness of the developed method. Furthermore， near-field simulation for a Delta Wing Body model demonstrates that， compared to conventional CFD method， the developed method reduces computational time by approximately 97.3%， while improving the precision of shock capturing. The developed method can provide support for rapid prediction of sonic boom and analysis of shock system evolution.

Key words: supersonic civil aircraft, sonic boom, sonic boom propagation, space-marching method, computational fluid dynamics

CLC Number:

V211.3

Liwen ZHANG, Zhonghua HAN, Keshi ZHANG, Ke SONG, Wenping SONG. High-fidelity numerical simulation of near-/mid-field sonic boom propagation using a space-marching method for supersonic civil aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(20): 531935.

Figures/Tables 16

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参数	文献［29］	文献［30］	文献［32］
控制方程	欧拉方程	欧拉方程	欧拉方程
计算网格	笛卡尔网格	结构网格	结构网格
求解框架	有限差分	有限差分	有限体积
坐标系	柱坐标系	曲线坐标系	曲线坐标系
推进方向空间离散格式	显式三阶四层有限差分近似方法^［33］	隐式线雅克比迭代	显式三步三阶龙格库塔^［34］
非推进方向空间离散格式	三阶DRP	四阶显式HWCNS^［27］、 Roe通量（三阶WENO）	AUSM+_UP、三阶MUSCL插值、 MinMod限制器

参数	绝对值最大值
I_x	2.7×10^-17
I_y	2.9×10^-17
I_z	2.8×10^-17

时间	传统CFD方法	本文发展方法
总计	23 h 40 min	39 min
时间推进数值模拟	23 h 40 min	24 min
流场插值		2 min
空间推进数值模拟		13 min

High-fidelity numerical simulation of near-/mid-field sonic boom propagation using a space-marching method for supersonic civil aircraft

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