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, Pages 285-313 PDF (1.61 M) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/amme.2008.39392 | ||
| 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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