A wing has a planform area S of 200 ft? and a total span b of 40 feet. The airfoils are symmetric all along the span. The airfoil has a 2-D lift curve slope of 21 per radian. The wing has a rectangular planform, and thus has zero taper. The wing is untwisted. a. Compute the lift coefficient C and the drag coefficient CDi at an angle of attack of 4 degrees. Use two terms in the series expansion for circulation. r= 2bV.[4, sin ø + A, sin 3ø] b. Repeat the above calculation, now with just one term IT=2bV»A1sino. Compare the lift drag coefficient CL and Co values to problem #2 above. c. Compare the results for drag coefficient from part (b) above with that for an elliptically loaded wing at this lift coefficient.
A wing has a planform area S of 200 ft? and a total span b of 40 feet. The airfoils are symmetric all along the span. The airfoil has a 2-D lift curve slope of 21 per radian. The wing has a rectangular planform, and thus has zero taper. The wing is untwisted. a. Compute the lift coefficient C and the drag coefficient CDi at an angle of attack of 4 degrees. Use two terms in the series expansion for circulation. r= 2bV.[4, sin ø + A, sin 3ø] b. Repeat the above calculation, now with just one term IT=2bV»A1sino. Compare the lift drag coefficient CL and Co values to problem #2 above. c. Compare the results for drag coefficient from part (b) above with that for an elliptically loaded wing at this lift 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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![A wing has a planform area \( S \) of 200 ft² and a total span \( b \) of 40 feet. The airfoils are symmetric all along the span. The airfoil has a 2-D lift curve slope of \( 2\pi \) per radian. The wing has a rectangular planform, and thus has zero taper. The wing is untwisted.
a. Compute the lift coefficient \( C_L \) and the drag coefficient \( C_{Di} \) at an angle of attack of 4 degrees.
Use two terms in the series expansion for circulation.
\[
\Gamma = 2bV_\infty \left[A_1 \sin \phi + A_3 \sin 3\phi\right]
\]
b. Repeat the above calculation, now with just one term \(\Gamma=2bV_\infty A_1 \sin\phi\).
Compare the lift drag coefficient \( C_L \) and \( C_D \) values to problem #2 above.
c. Compare the results for drag coefficient from part (b) above with that for an elliptically loaded wing at this lift coefficient.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Ff83af5dd-3182-4e6c-a1b5-32e4ba734fe8%2F42034442-b63e-4365-bd2d-a855ac7cd003%2F5ha8ik_processed.jpeg&w=3840&q=75)
Transcribed Image Text:A wing has a planform area \( S \) of 200 ft² and a total span \( b \) of 40 feet. The airfoils are symmetric all along the span. The airfoil has a 2-D lift curve slope of \( 2\pi \) per radian. The wing has a rectangular planform, and thus has zero taper. The wing is untwisted.
a. Compute the lift coefficient \( C_L \) and the drag coefficient \( C_{Di} \) at an angle of attack of 4 degrees.
Use two terms in the series expansion for circulation.
\[
\Gamma = 2bV_\infty \left[A_1 \sin \phi + A_3 \sin 3\phi\right]
\]
b. Repeat the above calculation, now with just one term \(\Gamma=2bV_\infty A_1 \sin\phi\).
Compare the lift drag coefficient \( C_L \) and \( C_D \) values to problem #2 above.
c. Compare the results for drag coefficient from part (b) above with that for an elliptically loaded wing at this lift coefficient.
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