Passive shock control concept for drag reduction in transonic flow

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[1] [1,Dietz, G.
来源：
Dietz, G. (Guido.Dietz@dlr.de) | 1600年 / American Institute of Aeronautics and Astronautics Inc.卷 / 42期
关键词：
Boundary layers - Drag - Pressure effects - Shock absorbers - Thickness measurement - Wakes - Wind tunnels - Wings;
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摘要：
The operating principle of the novel passive shock control concept for drag reduction on swept wings called D-Strips was introduced. Wind-tunnel experiments were conducted at transonic airspeeds using an airfoil VC-Opt 6s with forced boundary layer transition. Wake measurements demonstrated that, locally, in the wake of D-Strips the total drag increased. Results indicated that airscoop-type configurations might perform better as D-Strips than Velcro-type strips.
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