低声爆超声速客机声爆预测及不确定度量化分析

陈树生; 顾奕然; 杨华; 黄江涛; 高正红

doi:10.7638/kqdlxxb-2021.0373

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低声爆超声速客机声爆预测及不确定度量化分析

研究论文 | 更新时间：2026-05-28

- 低声爆超声速客机声爆预测及不确定度量化分析
- Sonic boom prediction and uncertainly quantification analysis of a low-boom super-sonic aircraft
- 空气动力学学报 2023年41卷第4期页码：41-51
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710072
  2. 中航工业第一飞机设计研究院,西安,710089
  3. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
  
  陈树生（1991-），男，福建泉州人，副教授，研究方向：计算流体力学，飞行动力学，飞行器设计. E-mail：sshengchen@nwpu.edu.cn
  高正红*（1960-），女，陕西西安人，教授，研究方向：空气动力学，飞行动力学，飞行器设计. E-mail：zgao@nwpu.edu.cn
- 基金信息：
  
  陕西省自然科学基金（2021JQ-076）
- DOI：10.7638/kqdlxxb-2021.0373
  中图分类号： TB533+.2;TB52+9
- 纸质出版：2023
- 稿件说明：
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陈树生, 顾奕然, 杨华, 等. 低声爆超声速客机声爆预测及不确定度量化分析[J]. 空气动力学学报, 2023, 41(4): 41−51.

CHEN Shusheng, GU Yiran, YANG Hua, et al. Sonic boom prediction and uncertainly quantification analysis of a low-boom super-sonic aircraft[J]. 2023, 41(4): 41-51.
陈树生, 顾奕然, 杨华, 等. 低声爆超声速客机声爆预测及不确定度量化分析[J]. 空气动力学学报, 2023, 41(4): 41−51. DOI： 10.7638/kqdlxxb-2021.0373

CHEN Shusheng, GU Yiran, YANG Hua, et al. Sonic boom prediction and uncertainly quantification analysis of a low-boom super-sonic aircraft[J]. 2023, 41(4): 41-51. DOI： 10.7638/kqdlxxb-2021.0373.

摘要

声爆精确预测问题是制约超声速客机技术突破的关键瓶颈之一。由于大气来流条件不断发生波动存在不确定性，为得到更可靠的声爆近/远场信号，需考虑来流参数的不确定性对声爆预测结果的影响，并甄别其中影响声爆预测的关键性因素，为工程实际应用提供有价值的参考。本文基于CFD声爆近场信号模拟和增广Burgers方程的声爆远场信号预测方法，对第三届声爆预测研讨会（SBPW-3）的C608低声爆超声速飞行器开展了声爆信号特性分析。首先，采用约5021万非结构混合网格半模计算了近场过压值，并研究了远场地面波形计算的时间和空间网格收敛性。接着，分析了基准状态下复杂近场流动特征及地面波形特征，通过与C608飞行器公开数据对比，验证了该方法和自研程序的准确度。此外，研究了不同物理模型和大气相对湿度对地面波形的影响。在此基础上，运用基于非嵌入式多项式混沌（NIPC）方法开展了对不同来流参数（来流马赫数、来流攻角和单位雷诺数）的不确定度量化分析和敏感性分析。结果表明，在给定的输入变量不确定度条件下，地面波形波峰与波谷处过压值变化明显。相比而言，来流单位雷诺数对地面波形过压值的影响显著低于来流马赫数和来流攻角的影响。

Abstract

Accurate prediction of sonic booms is one of the key bottlenecks restricting the breakthrough of supersonic aircraft technology. To obtain a more reliable near- and far-field signals of a sonic boom

it is necessary to consider the influence of the uncertainty of incoming flow parameters that fluctuate continuously. Moreover

key factors affecting the accurate prediction of sonic booms need to be identified to provide a valuable guideline for practical applications. In this paper

the sonic boom characteristics of the supersonic aircraft C608 provided by the 3rd sonic boom prediction workshop (SBPW-3) are analyzed based on the near-field signal simulation based on Computational Fluid Dynamics and the far-field signal prediction method based on the augmented Burgers equation. Firstly

the near-field over-pressure value is calculated using an unstructured hybrid grid with 50.21 million cells for half of the model

and the temporal and spatial grid convergence of far-field ground waveform is studied. Secondly

the complex near-field flow characteristics and ground waveform characteristics in the reference state are analyzed. Compared with the public data of aircraft C608

the accuracy of the method and the in-house-development program has been effectively verified. In addition

the effects of different physical models and atmospheric relative humidity on the ground waveform are also investigated. On this basis

the uncertainty quantification and sensitivity analysis of different incoming flow parameters (Mach number

angle of attack

and unit Reynolds number) are carried out by using the non-intrusive polynomial chaos (NIPC) and Sobol index method. The results show that

for a given uncertainty of input variables

the over-pressure values at the peak and trough of ground waveform differ significantly. In contrast

the influence of unit Reynolds number is significantly smaller than those of Mach number and angle of attack.

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references

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