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Effects of Various Fillet Shapes on a 76/40 Double Delta Wing from Mach 0.18 to 0.7The effects of linear, diamond, and parabolic fillets on a double delta wing were investigated in the NASA Langley 7 x 10 ft High Speed Tunnel from Mach 0.18 to 0.7 and angles of attack from 4 deg. to 42 deg. Force and moment, pneumatic pressures, pressure sensitive paint, and vapor screen flow visualization measurements were used to characterize the flow field and to determine longitudinal forces and moments. The fillets increased lift coefficient and reduced induced drag without significantly affecting pitching moment. Pressure sensitive paint showed the increase in lift is caused by an increase in suction and broadening of the vortex suction footprint. Vapor screen results showed the mixing and coalescing of the strake fillet and wing vortices causes the footprint to broaden.
Document ID
20040040232
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Gonzalez, Hugo A.
(Naval Air Systems Command Patuxent River, MD, United States)
McLachlan, Blair G.
(NASA Ames Research Center Moffett Field, CA, United States)
Erickson, Gary E.
(NASA Langley Research Center Hampton, VA, United States)
Bell, James H.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 21, 2013
Publication Date
March 1, 2003
Publication Information
Publication: Symposium on Advanced Flow Management. Part A: Vortex Flows and High Angle of Attack for Military Vehicles. Part B: Heat Transfer and Cooling in Propulsion and Power Systems
Subject Category
Aircraft Design, Testing And Performance
Distribution Limits
Public
Copyright
Other
Document Inquiry

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