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Unformatted text preview: Wing Taper Considerations Tapering a wing planform gives a number of significant aerodynamic and structural advan- tages, but it can also cause problems if overdone. Consider three AR = 10 wings of the same span and area, but different taper ratios λ = c tip /c root . When operated at some overall lift coeﬃcient C L , these wings have the L ′ ( y ) and c ℓ ( y ) distributions shown in Figure 1. c c c l l l C L L’ C L L’ C L e = 0.952 e = 0.990 L’ tip stall risk of L/b M o = 0.113 L/b M o L/b M o e L b = 0.100 = 0.971 λ = 1.0 L b λ = 0.5 L b = 0.107 λ = 0.2 Figure 1: Load distributions, root bending moment, and span eﬃciency for three taper ratios. All three cases have AR = 10, and no wing twist. Of the three wings, the most strongly tapered λ = 0 . 2 wing will have by far the smallest tip deﬂection ratio δ/b . This is mostly due to its larger root chord giving a greater local stiffness, although its smaller root bending moment factor of 0.100 also contributes. Such...
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
- Fall '05