Numerical Exploration of Solid Rocket Motor Blast Tube Flow Field

  • Afroz Javed Defence Research & Development Laboratory, Hyderabad
  • P. K. Sinha Defence Research & Development Laboratory, Hyderabad
  • Debasis Chakraborty Defence Research & Development Laboratory, Hyderabad
DOI: https://doi.org/10.14429/dsj.63.5763
Keywords: Blast tube, total pressure loss, computational fluid dynamics

Abstract

The blast tube flowfield of a solid rocket motor is explored numerically by solving 3-D RANS equations with SST Turbulence model using a commercial computational fluid dynamics (CFD) software CFX-10. Parametric studies are carried out to find out the effect of the blast tube diameter on the total pressure loss in the rocket motor. It is observed that the total pressure loss in the rocket motor is less than 4 per cent and the blast tube is contributing less than 1 per cent. It is also found out that higher the blast tube diameter, the lesser the drop in the total pressure. Blast tube geometry is not found to contribute significantly in the overall thrust and specific impulse in the rocket motor.

Defence Science Journal, 2013, 63(6), pp.616-621, DOI:http://dx.doi.org/10.14429/dsj.63.5763

Author Biographies

Afroz Javed, Defence Research & Development Laboratory, Hyderabad
Dr Afroz Javed did his MTech from Indian Institute of Technology (IIT) Madras, in 1996 and PhD from Indian Institute of Science (IISc), Bengaluru in 2013. Presently he is working in the Directorate of Computational Dynamics, Defence Research & Development laboratory (DRDl), Hyderabad. He has published 5 journal papers and 3 conference papers. His research interests include: Computational fluid dynamics (CFD), propulsion, combustion instability, and turbulent compressible mixing.
P. K. Sinha, Defence Research & Development Laboratory, Hyderabad
Mr Pradip Kumar Sinha has completed his BE from NIT, Durgapur and M.E. in Mechanical Engineering from Jadavpur university, Kolkata. He is working in the area of Computational Fluid Dynamics at Defence Research and Development laboratory, Hyderabad from 1990. He has contributed significantly in the development and application of indigenous Euler codes for missile aerodynamic characterization. He has received DRDO Young scientist award 1998. He has nearly 30 publications in various conferences and journals.
Debasis Chakraborty, Defence Research & Development Laboratory, Hyderabad
Dr Debasis Chakraborty obtained his PhD (Aerospace Engineering) from Indian Institute of Science (IISc), Bengaluru. Presently, he is working as Technology Director, Computational Fluid Dynamics (CFD), DRDl, Hyderabad. He was the guest editor of special issue of Defence Science Journal on CFD. His research areas includes: CFD, aerodynamics, high speed combustion and propulsion. He has more than 120 technical papers in referred journals and conferences.
Published
2013-12-18
How to Cite
Javed, A., Sinha, P., & Chakraborty, D. (2013). Numerical Exploration of Solid Rocket Motor Blast Tube Flow Field. Defence Science Journal, 63(6), 616-621. https://doi.org/10.14429/dsj.63.5763
Issue
Vol 63 No 6: Optical and Electro-Optical Instrumentation
Section
Aeronautical Systems
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