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Unformatted text preview: 1. Home Work Set #4 Problem #3 Hints Consider a symmetric airfoil, with a flap hinged at x= x f . This flap is deflected by an angle δ so that the camber line looks like the sketch below. You are asked to show that the lift generated by the flap deflection is given by: ( 29 [ ] ( 29 ( 29 σ σ δ σ σ δ σ σ π cos 1 2 1 : such that defined is where 1 cos sin 2 1 sin 2 2 4 / , = = + = f c m l x C C Solution: Let h be the height of the camber line at x= x f . Then, the slope of the camber line is given by: f x h dx dZ = for 0<x<x f (1a) ) 1 ( f x h dx dZ = for x f <x<1 (1b) Also, since (i) α is the angle between the chord line and the freestream, (ii) dZ/dx is the angle between the camber line and the chord line, it follows that line. camber mean the and freestream e between th Angle = dx dZ α For the first segment, from the figure below, this angle αdZ/dx is zero, and for the second segment this angle equals δ . Then, from the theory, ( 29 σ π π δ θ δ π θ π θ...
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This note was uploaded on 10/23/2011 for the course AE 3003 taught by Professor Yeung during the Fall '08 term at Georgia Tech.
 Fall '08
 Yeung

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