Analysis on typical parameters of bodies of revolution affecting the sonic boom

LENG Yan; QIAN Zhansen; LIU Zhongchen

doi:10.7638/kqdlxxb-2018.0291

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Analysis on typical parameters of bodies of revolution affecting the sonic boom

更新时间：2026-05-28

- Analysis on typical parameters of bodies of revolution affecting the sonic boom
- Vol. 37, Issue 4, Pages: 655-662, 689(2019)
- 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：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0291
  CLC： V211.3
- Published：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

WHITHAM G B. The flow pattern of a supersonic projectile[J]. Communications on Pure Applied Mathematics, 1952, 5(3):301-348.

WALKDER F. Theshock pattern of a wing-body combination, far from the flight path[J]. Aeronautical Quarterly, 1958, 9(2):164-194.

CARLSON H W. Simplified sonic-boom prediction[R]. NASA TP-1978-1122, 1978.

PLOTKIN J K. A rapid method for the computation of sonic booms[R]. AIAA 1993-4433, 1993.

YAMASHITA R, SUZUKI K. Full-field sonic boom simulation in real atmosphere[R]. AIAA 2014-2269, 2014.

YAMASHITA R, SUZUKI K. Full-field sonic boom simulation in stratified atmosphere[J]. AIAA Journal, 2016, 54(10):3223-3231.

KANDIL O A, YANG Z, BOBBITT P J. Prediction of sonic boom signature using Euler-full potential CFD with grid adaptation and shock fitting[R]. AIAA 2002-2542, 2002.

OZCERI A I. Sonic boom prediction using Euler/full potential methodology[R]. AIAA 2007-369, 2007.

BUSEMANN A. The relation between minimized drag and noise at supersonic speed[C]//Proceedings of the conference on high-speed aeronautics, Polytechnic Institute of Brooklyn, 1955: 133-144.

RYHMINGI L. The supersonic boom of a projectile related to drag and volume[J]. J. Aerospace Sciences, 1961, 28:113-118.

HAYES W D, HAEFILI R C, and KULSVUD H E. Sonic boom propagation in a stratified atmosphere, with computer program[R]. NASA CR-1299, 1969.

GEORGE A R, SEEBASS R. Sonic boom minimization including both front and rear shocks[J]. AIAA Journal, 1971, 9(10):2091-2093.

DARDEN C M. Minimization of sonic boom parameters in real and isothermal atmospheres[R]. NASA TND-7842, 1975.

HEARING E A Jr, MURRAY J E, PURIFOY D D, et al. Airborne shaped sonic boom demonstration pressure measurements with computational fluid dynamics comparisons[R]. AIAA 2005-0009, 2005.

PAWLOWSKI J W, GRAHAM D H, BOCCADORO C H, et al. Origins and overview of the shaped sonic boom demonstration program[R]. AIAA 2005-0005, 2005.

郭润兆, 无强波构型理论发展现状研究[J].航空工程进展, 2010, 11(14): 341-346.

KANDILO, KHASDEO N, OZCER I A. Sonic boom mitigation through thickness, camber and nose angle optimizations for a delta wing[R]. AIAA 2006-6636, 2006.

KANDILO, KHASDEO N, OZCER I A. Optimization of delta wing geometry parameters for sonic boom mitigation[R]. AIAA 2007-4109, 2007.

CARLSON H W, MACK R J, MORRIS O A. A wind-tunnel investigation of the effect of body shape on sonic-boompressure distributions[R]. NASA TN D-3160, November 1965.

SBROUT B L, MACK R J, DOLLYBIGB S M. A wind-tunnel investigation of sonic-boom pressure distributions of bodies of revolution at Mach 2.96, 3.83 and 4.63[R]. NASA TN D-6195, 1971.

LENG Y, QIAN Z S. Sonic boom signature prediction and analysis for a type of hypersonic long-range civil vehicle[R]. AIAA 2017-4422, 2017.

LI H M, QIAN Z S. Implementation of three different transition methods and comparative analysis of the results computed by OVERSET software[R]. AIAA 2016-3491, 2016.

LI X F, QIAN Z S. Applications of overset grid technique to CFD simulation of high Mach number multi-bodyinteraction/separation flow[C]//Proceeding of 2014 Asia-Pacific International Symposium on Aerospace Technology, Shanghai, China, August 22nd-24th, 2014.

LIU Y, WANG L, QIAN Z S. Numerical investigation on the assistant restarting method of variable geometry for high Mach number inlet[J]. Aerospace Science and Technology, 2018, 79:647-657.

THOMAS C L. Extrapolation of sonic boom pressure signatures by the waveform parameter method[R]. TND-6832, 1972.

THOMAS, C L. Extrapolation of wind-tunnel sonic boom signatures without use of a Whitham F-Function[R]. NASA SP-255, 1970.

PLOTKIN J K. Ground data collection of shaped sonic boom experiment aircraft pressure signature[R]. AIAA 2005-0010, 2005.

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