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At a pilot training school, an instructor
asked his students what is the takeoff speed required
for a specific aircraft when the angle of attack is set at 6o.
The aircraft, weighing 3,500 lbf, is assumed to be fully loaded
is provided by the aircraft manufacturer:
CL = 0.3(1 + 0.2α)
where CL is the lift coefficient and α is
the angle of attack in degrees.