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.

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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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A NACA 2412 airfoil with a chord of 0.64m is flying in an airstream of standard sea level conditions. The freestream velocity is 70 m/s. Given the lift per unit span is 1,254 N/m. By using the experimental data for NACA 2412 data plot in Figure Q1c, investigatethe angle of attack of the airfoil and the analyze the value of drag per unit spanof the airfoil. Given that at standard sea level, ?=1.789×10-5 kg/m.s.
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