airfoil with 2 spars
grabcad
Given airfoil coordinates, it was essential to determine skin thickness, spar number and their thickness, along with material choice. Spars protruded from the airfoil skin due to uneven spar placement in either direction. Using a shell feature proved unsuccessful, while extrude cut made adjusting individual element thicknesses difficult. Separate components for spars and skin would have been beneficial, particularly during material selection; however, mating them within an assembly was impractical. If you have alternative modeling suggestions, please share.
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