spl8a - Wing Taper Considerations Tapering a wing planform...

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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 ( 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 inherent stiffness allows the strongly tapered wing to have a larger span than the others,
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