文章基本信息

标题：Flow Around a Conical Nose with Rounded Tail Projectile for Subsonic, Transonic, and Supersonic Flow Regimes : A Numerical Study
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作者：Amitesh Kumar ; H. S. Panda ; T. K. Biswal 等
期刊名称：Defence Science Journal
印刷版ISSN：0976-464X
出版年度：2014
卷号：64
期号：6
页码：509-516
DOI：10.14429/dsj.64.8111
语种：English
出版社：Defence Scientific Information & Documentation Centre
摘要：Flow around a conical nose with rounded tail projectile has been studied numerically for subsonic, transonic and supersonic flow regimes. The conic angle of the projectile is 10°. The inflow Mach numbers are 0.5, 0.9, and 1.5. Axisymmetric Euler’s equations are solved for predicting the drag coefficient. It has been observed that even for a subsonic flow regime, the Mach number distribution is not uniform owing to the non-symmetric shape of the projectile. The predicted drag coefficients for subsonic, transonic, and supersonic cases are 0.018, 0.089, and 0.395, respectively. It was observed that rounded tail is a better option than boat tail so far drag force is concerned. Science Journal, Vol. 64, No. 6, November 2014, pp.509-516, DOI: http://dx.doi.org/10.14429/dsj.64.8111
关键词：Projectile, drag, supersonic flow, numerical modelling, nose angle