Question

1. A light airplane uses a NACA 4415 airfoil. It has a rectangular wing planform, with an area of
15.3 m' and a span of 10.2 m. The aircraft is flying at a gross weight of 7340 N.
(a) Neglecting any finite wing effects (induced drag) and assuming sea level conditions, at
what angle of attack will the aircraft be flying when its airspeed is 160 km/h?
(b) At 160 km/h, what is the profile drag of the wing? What reduction in drag could be achieved
if the wing made use of an NACA 642-415 airfoil?
(c) Still ignoring finite wing effects, with no flaps, what is the aircraft touchdown speed if the
pilot executes a "full stall" landing (the aircraft stalls just as the wheels touch the runway)?
Estimate how this speed changes if the pilot deploys split flaps which have a 0.3 m. chord,
5.1 m. in span, and deflect 60 degrees.​

Answer 1

Answer:

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