a) The mean camber line of an aerofoil is defined by the relations: Zc m x x X 2q C C C Zc= m с (1- x In the above, c is the aerofoil chord. Given that, m = 0.045, q = 0.25, and using thin aerofoil theory estimate: For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about the quarter-chord at -8° AOA are found to be -0.6 and -0.0466, respectively. At 6° AOA, these coefficients are found to be 0.86 and -0.0354, respectively. Giving reasons for your method, calculate the zero lift AOA and the location of the aerodynamic centre.
a) The mean camber line of an aerofoil is defined by the relations: Zc m x x X 2q C C C Zc= m с (1- x In the above, c is the aerofoil chord. Given that, m = 0.045, q = 0.25, and using thin aerofoil theory estimate: For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about the quarter-chord at -8° AOA are found to be -0.6 and -0.0466, respectively. At 6° AOA, these coefficients are found to be 0.86 and -0.0354, respectively. Giving reasons for your method, calculate the zero lift AOA and the location of the aerodynamic centre.
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
Question
![a) The mean camber line of an aerofoil is defined by the relations:
Zc
m
x
x
X
2q
C
C
C
Zc=
m
с
(1-
x
In the above, c is the aerofoil chord. Given that, m = 0.045, q = 0.25, and using thin
aerofoil theory estimate:](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F2f40e488-8d31-4ebf-93c2-8a5fabf31b11%2Fd1cd0376-1e23-45a7-b67a-117488ce2d7d%2Fbpf6cb_processed.png&w=3840&q=75)
Transcribed Image Text:a) The mean camber line of an aerofoil is defined by the relations:
Zc
m
x
x
X
2q
C
C
C
Zc=
m
с
(1-
x
In the above, c is the aerofoil chord. Given that, m = 0.045, q = 0.25, and using thin
aerofoil theory estimate:
![For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about
the quarter-chord at -8° AOA are found to be -0.6 and -0.0466, respectively. At 6° AOA,
these coefficients are found to be 0.86 and -0.0354, respectively.
Giving reasons for your method, calculate the zero lift AOA and the location of the
aerodynamic centre.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F2f40e488-8d31-4ebf-93c2-8a5fabf31b11%2Fd1cd0376-1e23-45a7-b67a-117488ce2d7d%2F06qca0e_processed.png&w=3840&q=75)
Transcribed Image Text:For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about
the quarter-chord at -8° AOA are found to be -0.6 and -0.0466, respectively. At 6° AOA,
these coefficients are found to be 0.86 and -0.0354, respectively.
Giving reasons for your method, calculate the zero lift AOA and the location of the
aerodynamic centre.
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