Flow Around a Conical Nose with Rounded Tail Projectile for Subsonic, Transonic, and Supersonic Flow Regimes : A Numerical Study

Defence Science Journal

T. K. Biswal²  Amitesh Kumar¹  H. S. Panda²  R. Appavuraj² 

[1] National Institute of Technology, Rourkela;Proof and Experimental Establishment, Chandipur

关键词: Projectile;    drag;    supersonic flow;    numerical modelling;    nose angle;   

DOI  :  

学科分类：社会科学、人文和艺术（综合）

来源: 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

【 授权许可】

Unknown