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
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This problem is an aerodynamics problem. I'm sorry, but please explain
![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 +αtw•
Assume the downwash is the same as the no-twist distribution over
the span. [낚시성 내용 포함]
a) Obtain the lift force versus angle of attack.
b) Obtain the induced drag coefficient.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F038a02db-4c58-490d-a514-8afd65e2eb41%2F38f36a3f-bd6f-48ec-9ea9-793811915bef%2Fljjxfrq_processed.png&w=3840&q=75)
Transcribed Image Text: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 +αtw•
Assume the downwash is the same as the no-twist distribution over
the span. [낚시성 내용 포함]
a) Obtain the lift force versus angle of attack.
b) Obtain the induced drag coefficient.
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