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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Question
![(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 = po 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.
U
Streamlines
u = U_ -- cos 22
2W²
+w
Viscous wake
=
-W
(b) Consider a thin flat plate at zero angle of attack in an airflow at
P∞ =
1.225 kg/m³, T∞ = 288 K and μ∞ 1.7894 x 10-5 kg/m/s.
The length of the plate is 2 m and the span is 0.5 m. Assume the
boundary layers on the plate are laminar throughout (on the upper
and lower surfaces both) where LBL(x)/x = 0.664/√√/Rex applies.
The freestream velocity is 100 m/s. Calculate the friction drag (Df)
of the first half of the plate (0 ≤ x ≤ 1 m); and then, that of the
second half (1 ≤ x ≤ 2 m).](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fc0eba744-2ca5-4b9b-b356-631e195ec79e%2Fea77c61e-51dc-47d8-ba99-019980097a9c%2Fe3sa8rr_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 = po 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.
U
Streamlines
u = U_ -- cos 22
2W²
+w
Viscous wake
=
-W
(b) Consider a thin flat plate at zero angle of attack in an airflow at
P∞ =
1.225 kg/m³, T∞ = 288 K and μ∞ 1.7894 x 10-5 kg/m/s.
The length of the plate is 2 m and the span is 0.5 m. Assume the
boundary layers on the plate are laminar throughout (on the upper
and lower surfaces both) where LBL(x)/x = 0.664/√√/Rex applies.
The freestream velocity is 100 m/s. Calculate the friction drag (Df)
of the first half of the plate (0 ≤ x ≤ 1 m); and then, that of the
second half (1 ≤ x ≤ 2 m).
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