A closed-loop wind tunnel has a test section of cross-section W =3 ft byH =5 ft and length L =4 m. An aerofoil with 21% thickness to chord ratioand a chord length of 0.52 m is mounted vertically in the test section andspans the entire height. If the measured lift and drag coefficients are C; =0.325 and Ca =0.0071, what is the lift coefficient after correcting for solidblockage, wake blockage and streamline curvature?Give your answer to 3 decimal places.

Answered: Image /qna-images/answer/86f6056c-93c6-4119-aa50-d02fb650f1e4.jpg

Answered: A closed-loop wind tunnel has a test…

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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The lift curve for the 4 digit NACA 2421 airfoil is shown in the Figure. Consider a wing with AR = 8, sweep ? = 15 ???, and airplane flies at the Mach number equal to 0.3. The Oswald efficiency span number ?1 = 0.95 Calculate the lift slope for the finite wing. Clearly show the formula and explanations in the solution.
Consider a wing with a linear AR of 8.0 and a taper of 0.5, the wing has a wingspan of 196 ft and a thin profile, a CL max of 1.6, estimate the maximum lift coefficient of the wing and the position in the chord of the profile when it enters in loss. Consider an arrow angle (1/4 of the chord) of 30 °
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- Study how the lift and drag varies with a change in angle of attack for a flat plate, symmetrical airfoil and asymmetrical airfoil when Re is below 50'000 and compare it to higher Re.
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