(a) 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 = p along the streamlines (dashed lines in the figure) and across the wake where the velocity was measured, calculate the friction drag coefficient Cp of the wing section.
(a) 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 = p along the streamlines (dashed lines in the figure) and across the wake where the velocity was measured, calculate the friction drag coefficient Cp 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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![(a) 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 Cp, of the wing
section.
Upo
ZA
Streamlines
u = U-L co
COS
+w
Viscous wake
'W
2w](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fb924e824-f7b8-486a-bee8-48b1feb67b77%2F4eabb47e-2b7d-46dd-943a-dfd9554ac722%2F7tctkos_processed.png&w=3840&q=75)
Transcribed Image Text:(a) 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 Cp, of the wing
section.
Upo
ZA
Streamlines
u = U-L co
COS
+w
Viscous wake
'W
2w
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