EXPERIMENTAL AND COMPUTATIONAL INVESTIGATION OF THE AERODYNAMICS OF A SUPERSONIC PROJECTILE WITH STREAMWISE SLOTS
A., I., A., F. (2008). EXPERIMENTAL AND COMPUTATIONAL INVESTIGATION OF THE AERODYNAMICS OF A SUPERSONIC PROJECTILE WITH STREAMWISE SLOTS. EKB Journal Management System, 13(13th International Conference on Applied Mechanics and Mechanical Engineering.), 285-313. doi: 10.21608/amme.2008.39392
IBRAHIM A.; FILIPPONE A.. "EXPERIMENTAL AND COMPUTATIONAL INVESTIGATION OF THE AERODYNAMICS OF A SUPERSONIC PROJECTILE WITH STREAMWISE SLOTS". EKB Journal Management System, 13, 13th International Conference on Applied Mechanics and Mechanical Engineering., 2008, 285-313. doi: 10.21608/amme.2008.39392
A., I., A., F. (2008). 'EXPERIMENTAL AND COMPUTATIONAL INVESTIGATION OF THE AERODYNAMICS OF A SUPERSONIC PROJECTILE WITH STREAMWISE SLOTS', EKB Journal Management System, 13(13th International Conference on Applied Mechanics and Mechanical Engineering.), pp. 285-313. doi: 10.21608/amme.2008.39392
A., I., A., F. EXPERIMENTAL AND COMPUTATIONAL INVESTIGATION OF THE AERODYNAMICS OF A SUPERSONIC PROJECTILE WITH STREAMWISE SLOTS. EKB Journal Management System, 2008; 13(13th International Conference on Applied Mechanics and Mechanical Engineering.): 285-313. doi: 10.21608/amme.2008.39392

EXPERIMENTAL AND COMPUTATIONAL INVESTIGATION OF THE AERODYNAMICS OF A SUPERSONIC PROJECTILE WITH STREAMWISE SLOTS

The International Conference on Applied Mechanics and Mechanical Engineering
Article 78, Volume 13, 13th International Conference on Applied Mechanics and Mechanical Engineering., May 2008, Page 285-313  XML PDF (1.61 MB)
Document Type: Original Article
DOI: 10.21608/amme.2008.39392
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Authors
IBRAHIM A.1; FILIPPONE A.2
1Egyptian Armed Forces.
2Lecturer, School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, U.K.
Abstract
ABSTRACT
The present paper investigates the effect of streamwise slots applied to the boattail
section of a projectile at supersonic speeds. Experimental work was performed to show
the effect of the slots on the drag at Mach numbers M=1.36, 1.65 and 1.83. A single
configuration of the slot pattern was used with two different slot widths (0.5mm and
2.0mm). The physics of the cavity flow was computationally investigated as well as the
effect of the slots on the overall aerodynamic drag. Unlike the case of streamwise slots
at transonic speeds, the suction and blowing mechanism is absent at supersonic
speeds. It was found that there is a significant base drag reduction due to the presence
of the streamwise slots. The reduction in total drag is modest when the width is
W=0.5mm. However, the experiments showed that the drag increases at Mach
numbers ranging from 1.36 to 1.83 for a slot width W=2.0mm.
Keywords
shock wave; Boundary layer; Base Drag; Streamwise Slots; Cavity Flow
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