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Question 1 a) The mean camber line of an aerofoil is defined by the relations: ZC C = q xx C) C , X C m 29- 2 ZC = (1-9)². X x 9 c (1-9)² C C m In the above, c is the aerofoil chord. Given that, m = 0.045, q = 0.25, and using thin aerofoil theory estimate: i) The lift coefficient when the angle of attack (AOA) is given as 3°. ii) The zero-lift AOA of the aerofoil. iii) The moment coefficient with respect to the leading edge and the centre of pressure when the AOA is given as 3°. MacBook

Question 1 a) The mean camber line of an aerofoil is defined by the relations: ZC C = q xx C) C , X C m 29- 2 ZC = (1-9)². X x 9 c (1-9)² C C m In the above, c is the aerofoil chord. Given that, m = 0.045, q = 0.25, and using thin aerofoil theory estimate: i) The lift coefficient when the angle of attack (AOA) is given as 3°. ii) The zero-lift AOA of the aerofoil. iii) The moment coefficient with respect to the leading edge and the centre of pressure when the AOA is given as 3°. MacBook

Elements Of Electromagnetics
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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Question 1 a) The mean camber line of an aerofoil is defined by the relations: ZC C = q xx C) C , X C m 29- 2 ZC = (1-9)². X x 9 c (1-9)² C C m In the above, c is the aerofoil chord. Given that, m = 0.045, q = 0.25, and using thin aerofoil theory estimate: i) The lift coefficient when the angle of attack (AOA) is given as 3°. ii) The zero-lift AOA of the aerofoil. iii) The moment coefficient with respect to the leading edge and the centre of pressure when the AOA is given as 3°. MacBook
Transcribed Image Text:Question 1 a) The mean camber line of an aerofoil is defined by the relations: ZC C = q xx C) C , X C m 29- 2 ZC = (1-9)². X x 9 c (1-9)² C C m In the above, c is the aerofoil chord. Given that, m = 0.045, q = 0.25, and using thin aerofoil theory estimate: i) The lift coefficient when the angle of attack (AOA) is given as 3°. ii) The zero-lift AOA of the aerofoil. iii) The moment coefficient with respect to the leading edge and the centre of pressure when the AOA is given as 3°. MacBook
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