MEM425F09.HW2.soln

# MEM425F09.HW2.soln - MEM 425 Aircraft Performance Design...

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Home work #2 solution Equations, and sections, used from text (you should know the development of these): Section 5.3.1, example 5.1 in particular, for Drag (=Thrust_required) .vs. Velocity plot. Equation 5.22 for analytical computation of the Drag_minimum velocity. Notice from this equation that this velocity is inversely proportional to sqrt(density), showing that the velocity increases with altitude, for fixed weight and a given aircraft. Section 5.6, example 5.7 in particular, for Power (=V*T) .vs. Velocity plot. Equation 5.41 for analytical computation of the Power_minimum velocity. Notice from this equation that this velocity also is inversely proportional to sqrt(density), showing that the velocity increases with altitude, for fixed weight and a given aircraft. ======================================================= Matlab code: % P_comp clear density weight = 2950; % weight in lbs area = 174; % wing area ft^2 span = 35.8; % wing span ft O_eff =

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MEM425F09.HW2.soln - MEM 425 Aircraft Performance Design...

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