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 ftlb/sec
.
The results are given below following the matlab code.
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 Spring '08
 Yousuff
 Mass, Aerodynamics, Velocity, Dmin

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