Experimental/Computational Study of 3D Swept Wings with Ice Accretions
In the fall of 2010, a long-term research project was initiated through funding provided by the Federal Aviation Administration on the effects of ice accretions on three-dimensional (swept) wings. The initial experiment began in the spring of 2011 at the University of Illinois in the 3 x 4 ft. subsonic wind tunnel using a scale semispan 3D wing modeled off of the NASA Common Research Model. Below are some images and flow visualization results from this initial wind tunnel experiment.
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Above are images of the internal frame for the 3D wing model installed in the 3 x 4 ft. wind tunnel. The frame was manufactured from a solid block of stainless steel using a 3D mill to ensure sufficient strength and minimal deflection and was designed for a stereo lithography (SLA) clamshell which provided the wing/airfoil shape. There also were tabs for mounting removable leading edges in order to test several different ice shapes.
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Above left is the frame fitted with the SLA wing pieces and pressure lines. Shown on the right is the complete model installed in the 3 x 4 ft. wind tunnel.
Below are a few images from the flow visualization runs at Reynolds numbers of 300,000 and 600,000 and several angles of attack.
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| Clean wing (Re = 3x105, α = 3 deg.) | Clean wing (Re = 3x105, α = 10 deg.) |
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| Clean wing (Re = 6x105, α = 5 deg.) | Clean wing (Re = 6x105, α = 12 deg.) |
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| Iced Wing (Re = 3x105, α = 4 deg.) | Iced wing (Re = 3x105, α = 10 deg.) |
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| Iced Wing (Re = 6x105, α = 5 deg.) |
The students working on the project posing with the installed wing model: (from left to right) Jeff Diebold, Cassie Meisner, Andrew Mortonson and Joe Bottalla (not pictured). The initial results from this experiment will be presented in the future but additional information on the project can be found on the current research page here