[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

Journal of Projectiles, Rockets, Missiles and Guidance >

2018 , Vol. 38 >Issue 2: 65 - 68,73

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2018.02.015

A Method to Predict Aerodynamic Characteristics for Subsonic Missile

  • WANG Gang ,
  • LIU Junsheng ,
  • WANG Kun ,
  • ZHAO Junmin ,
  • YANG Yungang
Expand
  • Xi'an Modern Control Technology Research Institute, Xi'an 710065, China

Received date: 2017-10-21

  Online published: 2025-05-28

Fold

Abstract

Accurate and economical estimates of the aerodynamic characteristics are vital for missile preliminary design. A rapid mediumfidelity method is presented to predict the aerodynamics of subsonic missiles. The vortex lattice method is used to calculate the lift, center of pressure, tail fin efficiency as well as dynamic derivatives. The missile drag is component based and accounts for the wing drag and fuselage drag. A tactical missile is studied as a case. The analysis indicates the maximum error of aerodynamic parameters is within 15% over the flight Mach number range of 0. 3 to 0.6, angle of attack from 0 to 8deg and the time penalty of a single operating condition is less than 20 seconds. The results confirm both accuracy and efficiency of the proposed numerical method.

Key words： tactical missile; conceptual design; subsonic flow; aerodynamic characteristics

Cite this article

WANG Gang , LIU Junsheng , WANG Kun , ZHAO Junmin , YANG Yungang . A Method to Predict Aerodynamic Characteristics for Subsonic Missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018 , 38(2) : 65 -68,73 . DOI: 10.15892/j.cnki.djzdxb.2018.02.015

[an error occurred while processing this directive]

References

[1]
BLAKE W B Missile DATCOM user's manual-1997 Fortran 90 version: AFRL-VA-WP-TR-1998-3009[R]. Ohio: Wright-Patterson Air Force Research Laboratory, 1998.
[2]
MOORE F G, MCLNVILLE R M, HYMER T C. The 1998Version of the NSWC aeroprediction code, Part I: summaryof new theoretical methodology: NSWCDD/TR-98/1[R]. Dahlgren: Naval Surface Warfare Center Dahlgren Division, 1998.
[3]
АТТА Е Н Numerical simulation of missiles flow fields: AIAA-92-4353-CP[R]. Reston: AIAA, 1992.
[4]
张瑞民, 时晓天. 有翼导弹动态气动特性数值研究[J]. 弹箭与制导学报, 2017, 37(1): 117-420.
[5]
MELIN T A vortex lattice MATLAB implementation for lin-ear aerodynamic wing applications[D]. Stockholm: RoyalInstitute of Technology, 2000.
[6]
徐敏, 安效民. 飞行器空气动力特性分析与计算方法[M]. 西安: 西北工业大学出版社, 2012: 97-106.
[7]
张锡金. 飞行设计手册:气动设计[M]. 北京: 航空工业出版社, 2002: 269-270.
[8]
米百刚, 詹浩, 朱军. 基于CFD 数值仿真技术的飞行器动导数计算. 空气动力学报, 2014, 32(6): 834-839.
[9]
RONCH A D, VALLESPIN D, GHOREYSHI M, et al. E-valuation of dynamic derivatives using computational fluiddynamics[J]. AIAA Journal, 2012, 50(2): 470-484.
[10]
TAIRA K, ROWLEY C W, COLONIUS T, et al. Lift en-hancement for low-aspect ratio wings with periodic excita-tion[J]. AIAA Journal, 2010, 48(8): 1785-4790.
Options
Outlines

/

〈 〉

[an error occurred while processing this directive]