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

  • Amitesh Kumar National Institute of Technology, Rourkela
  • H. S. Panda Proof and Experimental Establishment, Chandipur
  • T. K. Biswal Proof and Experimental Establishment, Chandipur
  • R. Appavuraj Proof and Experimental Establishment, Chandipur
DOI: https://doi.org/10.14429/dsj.64.8111
Keywords: Projectile, drag, supersonic flow, numerical modelling, nose angle

Abstract

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

Author Biographies

Amitesh Kumar, National Institute of Technology, Rourkela
Dr Amitesh Kumar is an Assistant Professor in the Deptt. of Mechanical Engineering at the National Institute of Technology Rourkela, India. He received his MTech and PhD in Mechanical Engineering from Indian Institute of Technology Kharagpur, West Bengal, India. His main research interests are computational fluid dynamics, computing high Mach number flows, turbulent flows, and laser materials processing. He has published more than 32 articles in the journals and conference proceedings.
H. S. Panda, Proof and Experimental Establishment, Chandipur
Dr Himanshu Shekhar Panda received his MTech and PhD in Mechanical Engineering from IIT Kharagpur. Presently he is working as scientist-‘E’ at PXE, DRDO, India. His research areas includes : Experimental ballistics, computational fluid dynamics, spectral methods for scientific computing, microchannel flows in MEMS devices. Currently he is involved in high-speed flow visualisation and analysis and experimental impact dynamics studies. He is a Member of ADMB Panel under Armament Research Board.
T. K. Biswal, Proof and Experimental Establishment, Chandipur
Mr Tapan Kumar Biswal is currently working as a scientist at Proof & Experimental Establishment, Chandipur. He has 30 years of experience in the domain of high-speed imaging and photonics. His research interests include high-speed imaging and sensors.
R. Appavuraj, Proof and Experimental Establishment, Chandipur
Mr R. Appavuraj did his BE (Aeronautical Engineering) from Madras Institute of Technology, Chennai in 1982 and postgraduation from IIT-Madras, Chennai in 1984. Presently, he is Scientist-H and Director of Proof and Experimental Establishment (PXE), Chandipur. He has established the state-of-the-art Range Safety Simulation Model using soft computing techniques at ITR. He has published 30 conference papers and five research papers. He is recepient of ‘DRDO Scientist of the Year Award’ in 2012 for his contribution towards development of real-time flight safety expert system.
Published
2014-11-01
How to Cite
Kumar, A., Panda, H., Biswal, T., & Appavuraj, R. (2014). Flow Around a Conical Nose with Rounded Tail Projectile for Subsonic, Transonic, and Supersonic Flow Regimes : A Numerical Study. Defence Science Journal, 64(6), 509-516. https://doi.org/10.14429/dsj.64.8111
Issue
Vol 64 No 6: Test and Evaluation of Armaments
Section
Special Issue Papers
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