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Aero Assignment Nr. 5
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  Delft University of Technology AE4130 - Aircraft Aerodynamics Assignment 5: Winglet Design Ole Pfeifle 4206150 October 4, 2016  Contents 1 Introduction  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .  12 Methodology  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .  2 2.1 Winglet parametrization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22.2 AVL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3 Design and Analysis  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .  4 3.1 Cant angle effect on induced drag . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43.2 Cant angle effect on structural weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53.3 Optimization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 4 Conclusion and Recommendations  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .  7Appendix A Python script - AVL loop for optimization  . . . . . . . . . . . . . . . . . .  8  1 Introduction Most modern aircraft’s appearance is similar to previous generation. The same, proven aerodynamicconcepts are used and there seems to be little room for optimization, as more radical concepts oftencome with structural or other problems. One recent development however, are the use of winglets.By reducing the tip vortex winglets are capable of achieving a considerable decrease in drag. Theyeffectively create a wing who is closer to an infinite wing and has an increased effective aspect ra-tio. Without increasing the wing span, this can be very advantageous, making the winglet shape aninteresting part for research and optimization.This report looks at the effect that different winglet parameters have on the overall induced wing drag.The addition of a winglet obviously also changes the lift and force distribution over the wing and canlead to a heavier structure. The existence of an optimum is investigated and different optimizationparameters employed to find an ideal combination of winglet parameters.1  2 Methodology 2.1 Winglet parametrization For the winglets seven parameters are used to describe its geometry. The parameters used are asfollows:   root chord  C  w r   taper ratio  λ w   length  l w   leading edge sweep angle Λ w   cant angle  φ   twist (toe out) angle at root  ε w r   twist (toe out) angle at tip  ε w t The parameters are illustrated in Figure 1 together with the initial planform dimensions.Figure 1: Winglet design parameters and wing planform2
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