A wing section with a chord of c and a span of b is mounted at zero angle of attack in a wind tunnel. A pitot probe is used to measure the velocity profile in the viscous region downstream of the wing section as shown in the figure. The measured velocity profile is u(z) = U∞ - (U/2) cos[TZ/(2w)] for -w ≤ z≤ w. Here, w = 0.02c. Assuming a constant pressure p = Poo along the streamlines (dashed lines in the figure) and across the wake where the velocity was measured, calculate the friction drag coefficient CD, of the wing section.
A wing section with a chord of c and a span of b is mounted at zero angle of attack in a wind tunnel. A pitot probe is used to measure the velocity profile in the viscous region downstream of the wing section as shown in the figure. The measured velocity profile is u(z) = U∞ - (U/2) cos[TZ/(2w)] for -w ≤ z≤ w. Here, w = 0.02c. Assuming a constant pressure p = Poo along the streamlines (dashed lines in the figure) and across the wake where the velocity was measured, calculate the friction drag coefficient CD, of the wing section.
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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