Computational Investigation of Base Drag Reduction for a Projectile at Different Flight Regimes
Suliman, M., Mahmoud, O., Al-Sanabawy, M., Abdel-Hamid, O. (2009). Computational Investigation of Base Drag Reduction for a Projectile at Different Flight Regimes. EKB Journal Management System, 13(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT- 13, May 26 – 28, 2009), 1-13. doi: 10.21608/asat.2009.23743
M. A. Suliman; O. K. Mahmoud; M. A. Al-Sanabawy; O. E. Abdel-Hamid. "Computational Investigation of Base Drag Reduction for a Projectile at Different Flight Regimes". EKB Journal Management System, 13, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT- 13, May 26 – 28, 2009, 2009, 1-13. doi: 10.21608/asat.2009.23743
Suliman, M., Mahmoud, O., Al-Sanabawy, M., Abdel-Hamid, O. (2009). 'Computational Investigation of Base Drag Reduction for a Projectile at Different Flight Regimes', EKB Journal Management System, 13(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT- 13, May 26 – 28, 2009), pp. 1-13. doi: 10.21608/asat.2009.23743
Suliman, M., Mahmoud, O., Al-Sanabawy, M., Abdel-Hamid, O. Computational Investigation of Base Drag Reduction for a Projectile at Different Flight Regimes. EKB Journal Management System, 2009; 13(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT- 13, May 26 – 28, 2009): 1-13. doi: 10.21608/asat.2009.23743

Computational Investigation of Base Drag Reduction for a Projectile at Different Flight Regimes

International Conference on Aerospace Sciences and Aviation Technology
Article 69, Volume 13, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT- 13, May 26 – 28, 2009, May 2009, Page 1-13  XML PDF (1.1 MB)
Document Type: Original Article
DOI: 10.21608/asat.2009.23743
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Authors
M. A. Suliman1; O. K. Mahmoud2; M. A. Al-Sanabawy2; O. E. Abdel-Hamid2
1Ph. D Student, Kararry University, Khartoum, Sudan.
2Egyptian Armed Forces, MTC.
Abstract
A computational investigation for the 155mm artillery shell was conducted for the purpose of reducing the base drag. Three case studies were conducted to investigate the properties of the flow field around the shell for the flight at different Mach numbers at zero angle of attack. The three cases were: a shell with boattail, a shell with base cavity and a shell with base bleed. Also, combinations of these three cases were investigated. The higher drag reduction was demonstrated when using a combination of the three effects. For this latter case it was possible to realize a drag coefficient reduction of ~60% at subsonic regime and ~20 - 30% .at transonic and supersonic regimes. Based on the present methodology, a design
optimization for minimum drag can be applied on similar flying bodies.
Keywords
Aerodynamics; Computational Fluid Dynamics; Base Drag; projectile; boattail; base cavity; base bleed
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