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MEM425F10.HW2.soln

# MEM425F10.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. To compute stall velocities, use equation (5.67). For velocity limits enforced by power limitation proceed as: The two real roots of te above equation would yield the maximum and minimum velocities at different altitudes. Note: Power available to aircraft is Prop_efficiency times the engine power. Use the conversion 1hp = 550 ft-lb/sec . The results are given below following the matlab code.

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MEM425F10.HW2.soln - MEM 425 Aircraft Performance Design...

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