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

Info iconThis preview shows page 1. Sign up to view the full content.

View Full Document Right Arrow Icon
This is the end of the preview. Sign up to access the rest of the document.

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...
View Full Document

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.

Ask a homework question - tutors are online