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Improved Stall Prediction for Swept Wings Using Low-Order Aerodynamics.

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Figure

Figure 1.1:The linear and post-stall regions.
Figure 1.2: NACA 4415 airfoil at α = 30◦. This α is much greater than αstall, and there is alarge amount of separation over the upper surface.
Figure 1.3:Coverage of A330 simulator models, compared to actual AF447 data [1]
Figure 2.1:Geometry generation using OpenVSP
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Outline

Physics-based predictive approach

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