The Department of Aerospace Engineering at the University of Maryland has completed a research study for NASA Langley on the application of drooped leading edges to high aspect wings. The experimental study conducted for this grant was a natural extension of work previously conducted at NASA Ames, the University of Michigan, NASA Langley and the University of Maryland. Previous research had shown that wing planform modifications (commonly referred to as drooped leading edge mods) could have a significant effect on reducing or eliminating the stall/spin characteristics of General Aviation (GA) aircraft. All aircraft studied in the earlier work had relatively low aspect ratio wings (AR = 6). Since future GA aircraft will feature higher aspect ratio wings, the obvious question was: how well will the dropped leading edge work on higher aspect ratio wings. The focus of the current study was to examine the effectiveness of the drooped leading edge modifications to higher aspect ratio wings with AR = 9 to 12.
Studies in General Aviation Aerodynamics
1990
20 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Test Facilities & Equipment , Aerodynamic characteristics , Drooped airfoils , General aviation aircraft , Low aspect ratio wings , Wind tunnel apparatus , Wind tunnel tests , Wing planforms , Strain gage balances , Aerodynamic stalling , Aerospace engineering , Aircraft spin , Aspect ratio , Design analysis , Flow visualization , Leading edges
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