超声速条件下旋成体声爆典型影响因素分析

冷岩; 钱战森; 刘中臣

doi:10.7638/kqdlxxb-2018.0291

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超声速条件下旋成体声爆典型影响因素分析

专栏——声爆研究 | 更新时间：2026-05-28

- 超声速条件下旋成体声爆典型影响因素分析
- Analysis on typical parameters of bodies of revolution affecting the sonic boom
- 空气动力学学报 2019年37卷第4期页码：655-662, 689
- 作者机构：
  
  1. 航空工业空气动力研究院,沈阳,110034
  2. 高速高雷诺数气动航空科技重点实验室,沈阳,110034
- 作者简介：
  
  冷岩(1986-), 女, 黑龙江人, 工程师, 研究方向:声爆预测技术.E-mail:why1003why1104@sina.com
- 基金信息：
  
  国家自然科学基金项目（11672280）
- DOI：10.7638/kqdlxxb-2018.0291
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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冷岩, 钱战森, 刘中臣. 超声速条件下旋成体声爆典型影响因素分析[J]. 空气动力学学报, 2019, 37(4): 655-662, 689.

LENG Yan, QIAN Zhansen, LIU Zhongchen. Analysis on typical parameters of bodies of revolution affecting the sonic boom[J]. 2019, 37(4): 655-662, 689.
冷岩, 钱战森, 刘中臣. 超声速条件下旋成体声爆典型影响因素分析[J]. 空气动力学学报, 2019, 37(4): 655-662, 689. DOI： 10.7638/kqdlxxb-2018.0291.

LENG Yan, QIAN Zhansen, LIU Zhongchen. Analysis on typical parameters of bodies of revolution affecting the sonic boom[J]. 2019, 37(4): 655-662, 689. DOI： 10.7638/kqdlxxb-2018.0291.

摘要

声爆问题是制约未来超声速客机进入真正商业运营的关键技术之一。航空工业气动院发展了基于近场CFD模拟和远场传播模型相结合的混合声爆数值预测平台ARI_Boom，基于典型旋成体模型。在

=1.41~6.0范围内，研究了飞行参数和外形参数对地面声爆特征（包括最大过压和特征正冲量）的影响。首先给出了ARI_Boom预测平台计算方法介绍，并通过典型算例对其进行验证；其次，基于所建立平台研究了飞行参数和外形参数对地面声爆特征影响。结果表明：针对所研究构型，减小半锥角、减小长细比、降低飞行马赫数和提高飞行高度均能减弱地面声爆特征；随着钝度系数的增加，最大过压先减小后增加，并存在最佳钝度。

Abstract

Sonic boom is one of the key technologies for supersonic aircraft

particularly with regard to commercial air transport. The ARI_Boom in house code was used based on the near-field CFD simulation and far-field propagation model. Based on bodies of revolution

several flight and shape parameters were considered for investigating their effects on the sonic boom signature including overpressure and impulse. Mach numbers were varied from 1.41 to 6.0 due to some wind tunnel and flight tests results available for reference. Firstly

the method which used by the ARI_Boom was given and verified by a typical case. Secondly

flight and shape parameters were considered for investigating their effects on the sonic boom based on the ARI_Boom. According to the parametric analysis

it is found that sonic boom can be reduced by increasing flight altitude

decreasing cone half-angle

increasing fineness ratio or decreasing Mach number. However

with the increase of bluntness parameter

overpressure first decreases and then increases.

关键词

Keywords

references

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