For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about the quarter-chord at -8° AOA are found to be -0.598 and -0.0466, respectively. At 6° AOA, these coefficients are found to be 0.858 and -0.0354, respectively. Giving reasons for your method, calculate the zero lift AOA and the location of the aerodynamic centre.

Advanced Engineering Mathematics
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Author:Erwin Kreyszig
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Chapter2: Second-order Linear Odes
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For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about
the quarter-chord at -8° AOA are found to be -0.598 and -0.0466, respectively. At 6°
AOA, these coefficients are found to be 0.858 and -0.0354, respectively.
Giving reasons for your method, calculate the zero lift AOA and the location of the
aerodynamic centre.
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 -0.598 and -0.0466, respectively. At 6° AOA, these coefficients are found to be 0.858 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:
X X
17²7 ( 29 - *) * 2 * ²
2
q
с C с
Zc m
C
Zc
C
m
(1-q)²
≤q,
X
(1-9)²-( \ / -9
9
C
Given that, c is the aerofoil chord, m = 0.025, q = 0.45, and using thin aerofoil theory
estimate:
Transcribed Image Text:a) The mean camber line of an aerofoil is defined by the relations: X X 17²7 ( 29 - *) * 2 * ² 2 q с C с Zc m C Zc C m (1-q)² ≤q, X (1-9)²-( \ / -9 9 C Given that, c is the aerofoil chord, m = 0.025, q = 0.45, and using thin aerofoil theory estimate:
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