In this paper, we present a static aeroelastic analysis of a wind tunnel test model of a wing in high-lift configuration using a viscous flow simulation code. The model wing was tailored to deform during the tests by amounts similar to a composite airliner wing in high-lift conditions. This required use of a viscous flow analysis to predict the lift coefficient of the deformed wing accurately. We thus utilized an existing static aeroelastic analysis framework that involves an inviscid flow code (Cart3D) to predict the deformed shape of the wing, then utilized a viscous flow code (Overflow) to compute the aerodynamic loads on the deformed wing. This way, we reduced the cost of flow simulations needed for this analysis while still being able to predict the aerodynamic forces with reasonable accuracy. Our results indicate that the angle of attack of wing sections along the span decrease due to the induced washout deformation when the wing is aerodynamically loaded. While this induced washout decreases the lift until around an angle of attack of 16 degrees due to the reduction on angle of attack, it increases the lift at angles of attack more than 16 degrees by alleviating separation.
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