Reference 12 contains inviscid theory calculations for the upper and lower surface velocity distributions V(x) over an airfoil, where x is the chordwise coordinate. A typical re- sult for small angle of attack is as follows: xlc VIU„(upper) VIU„(lower) 0.0 0.0 0.0 0.025 0.97 0.82 0.05 1.23 0.98 0.1 1.28 1.05 1.13 0.2 1.29 0.3 1.29 1.16 0.4 1.24 1.16 0.6 1.14 1.08 0.8 0.99 0.95 1.0 0.82 0.82 Use these data, plus Bernoulli's equation, to estimate (a) the lift coefficient and (b) the angle of attack if the airfoil is symmetric.
Reference 12 contains inviscid theory calculations for the upper and lower surface velocity distributions V(x) over an airfoil, where x is the chordwise coordinate. A typical re- sult for small angle of attack is as follows: xlc VIU„(upper) VIU„(lower) 0.0 0.0 0.0 0.025 0.97 0.82 0.05 1.23 0.98 0.1 1.28 1.05 1.13 0.2 1.29 0.3 1.29 1.16 0.4 1.24 1.16 0.6 1.14 1.08 0.8 0.99 0.95 1.0 0.82 0.82 Use these data, plus Bernoulli's equation, to estimate (a) the lift coefficient and (b) the angle of attack if the airfoil is symmetric.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
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Problem 1.1MA
Related questions
Question
![Reference 12 contains inviscid theory calculations for the
upper and lower surface velocity distributions V(x) over an
airfoil, where x is the chordwise coordinate. A typical re-
sult for small angle of attack is as follows:
xlc
VIU„(upper)
VIU„(lower)
0.0
0.0
0.0
0.025
0.97
0.82
0.05
1.23
0.98
0.1
1.28
1.05
1.13
0.2
1.29
0.3
1.29
1.16
0.4
1.24
1.16
0.6
1.14
1.08
0.8
0.99
0.95
1.0
0.82
0.82
Use these data, plus Bernoulli's equation, to estimate
(a) the lift coefficient and (b) the angle of attack if the
airfoil is symmetric.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fd6fc524a-dd23-44d7-afa6-9e54bf2dd29f%2Fba1ecf95-ea7d-4834-82f8-fb2344ac3949%2Fy7fychj.png&w=3840&q=75)
Transcribed Image Text:Reference 12 contains inviscid theory calculations for the
upper and lower surface velocity distributions V(x) over an
airfoil, where x is the chordwise coordinate. A typical re-
sult for small angle of attack is as follows:
xlc
VIU„(upper)
VIU„(lower)
0.0
0.0
0.0
0.025
0.97
0.82
0.05
1.23
0.98
0.1
1.28
1.05
1.13
0.2
1.29
0.3
1.29
1.16
0.4
1.24
1.16
0.6
1.14
1.08
0.8
0.99
0.95
1.0
0.82
0.82
Use these data, plus Bernoulli's equation, to estimate
(a) the lift coefficient and (b) the angle of attack if the
airfoil is symmetric.
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