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Hershey bar wing vs composite wing - how much drag?
("Wayne Paul" wrote)
It is much easier to build a laminar flow airfoil and complex shaped wing to fuselage transition using composite construction. These wing have a better lift to drag ratio. The decrease in drag aerodynamic drag of the wing and static drag decrease associated with the wing/fuselage transition allow faster speeds. Can you reword this (for some of us "Huh?" lurkers) especially the wing to fuselage transition part? How good/efficient are Cherokee, Ercoupe, Cessna (aluminum & rivet) wing root fairings vs. what could be achieved with complex composite shapes? Same question with the wing shape - to hold up the same plane, ALL else being equal? So ballpark - how much more efficient would the use of complex composite construction (wings and wing root transition areas) make these planes - ALL else being equal? WAG - same power, weight, fuselage, etc - what improvements would these planes see in speed, climb, stall, or fuel burn numbers? Thanks. Montblack |
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