(b) Consider a thin flat plate at zero angle of attack in an airflow at Poo = 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).
(b) Consider a thin flat plate at zero angle of attack in an airflow at Poo = 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).
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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Please just solve for question (b)
i will be extremly appreciate!!!!!
![(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%2Fb924e824-f7b8-486a-bee8-48b1feb67b77%2F506ee44c-aa87-4036-a41b-9a5d0ce89c43%2F4976fs7f_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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