Engineering
Engineering, 12.12.2019 05:31, aidy3259

The camber line of a thin airfoil is given by ( z c ) = m ( x c ) (1 − ( x c ) 2 ), where m is a constant. (a) calculate the lift coefficient as a function of m and . (b) calculate the zero-lift angle of attack as a function of m. (c) calculate the pitching moment coefficient about the quarter-chord as a function of m. (d) plot cl, cm, c/4, and l=0 as a function of m. what conclusions can we make about the effect of camber? (e) do you think there will be agreement between your plots and experimental data for all values of m? why or why not?

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The camber line of a thin airfoil is given by ( z c ) = m ( x c ) (1 − ( x c ) 2 ), where m is a con...

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