Airfoil Tests with and without Control (Task 3)
Abstract
The aims of the present studies were to investigate, experimentally, the effect of passive control of shock boundary layer interactions on the design and off-design performance of airfoils. The investigation concentrated on airfoils designed to achieve large extents of natural laminar flow on both surfaces, since airfoils of this kind have a larger potential for improvement at design conditions, where shock waves are probably already present, and, in addition, have smaller margins as far as drag-rise and buffet boundaries are concerned when compared to turbulent designs. During the course of the investigation, having perused early results, it was agreed that DLR would retest the original airfoil VA-2 which had demonstrated the benefits of passive control [1.3].
Keywords
Reynolds Number Mach Number Wind Tunnel Lift Coefficient Viscous DragPreview
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References
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