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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.

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
Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
Section: Chapter Questions
Problem 1RQ
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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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