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Using the equations from thin aerofoil theory, evaluate the centre of pressure at angle of attack a = 5 for the aerofoil with the following
Using the equations from thin aerofoil theory, evaluate the centre of pressure at angle of attack a for the aerofoil with the following camber line zxxx for x Use the theoretical value for the location of aerodynamic centre.
Using the equations from thin aerofoil theory, evaluate the centre of pressure at
angle of attack a for the aerofoil with the following camber line
zxxx for x
Use the theoretical value for the location of aerodynamic centre.
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