18.2 Consider an elliptic-planform wing with an aspect ratio of 8. (Root chord=c, span=2b) The airfoil section is thin and symmetric, but the planform has geometrical twist, a(y)=-4(y/b) degrees, along the Span direction. The geometric angle of attack is geometrical = a +atw• Assume the downwash is the same as the no-twist distribution over the span. [³ 48 20 a) Obtain the lift force versus angle of attack. b) Obtain the induced drag coefficient.

18.2 Consider an elliptic-planform wing with an aspect ratio of 8. (Root chord=c, span=2b) The airfoil section is thin and symmetric, but the planform has geometrical twist, a(y)=-4(y/b) degrees, along the Span direction. The geometric angle of attack is geometrical = a +atw• Assume the downwash is the same as the no-twist distribution over the span. [³ 48 20 a) Obtain the lift force versus angle of attack. b) Obtain the induced drag coefficient.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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