HW8 - 1 , 4 / mc c 1 , L , , , , 1 , cp x 2 , l c 2 , 4 /...

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AAE 334, Fall 2011, Homework 8 Due Monday, September 12 at the beginning of class. 1. Show mathematically the effects of scaling airfoil camber on lift coefficient, quarter- chord moment coefficient, and center of pressure at the same angle of attack? That is, if one airfoil has camber of and another has camber of () x z c ( ) x z a c where a is a positive constant, how do the lift coefficients, quarter-chord moment coefficients, and centers of pressure compare? Call the results for the first airfoil , , and . 1 , l c 1 , 4 / mc c 1 , cp x 2. Similarly, what if you add together two cambers, ( ) ( ) x z x z c c 2 1 + which individually have performance or characteristics , , 1 , l c
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Unformatted text preview: 1 , 4 / mc c 1 , L , , , , 1 , cp x 2 , l c 2 , 4 / mc c 2 , L , and . Show what can you determine regarding the new values of , , 2 , cp x l c 4 / mc c L , and ? cp x Note: in recent years some students would assume a function for ( ) x z c and demonstrate the effects of one specific case. This falls far short of the goal here proving the impact of changes for all camber lines. Thus you are to work with the unknown and very general , not one example of . You do, however, assume that all airfoils under consideration satisfy the assumptions for thin airfoil theory. ( ) x z c ( ) x z c...
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