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P) Calculate the roll damping coefficient Clp for an airplane which has tip chord =1.5m, root chord =2.5m, and three-dimensional wing lift slope =0.07deg1. [
P) Calculate the roll damping coefficient Clpfor an airplane which has tip chord =1.5m, root chord =2.5m, and three-dimensional wing lift slope =0.07deg1. \[ -0.5849 \mathrm{rad}^{-1} \]
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