piper cherokee wing area is 16m², span is 9.75m. total weight is 1100kg. airfoil is NACA...

piper cherokee wing area is 16m², span is 9.75m. total weight is 1100kg. airfoil is NACA 65-415 and lift coefficient slope is 0.1033 per degree. αL=0 is -1.5degree. Assume τ = 0.12. when air density is 1.23Kg/m³ and speed is 193Km/h. Determine the wing's angle of attack

Expert Solution

Let the angle of attack be degrees.

The lift coefficient is given by

The lift force is given by

V= velocity=193x1000/3600=53.61 m/s

1.23 kg/m³ (density)

S= wing area= 16 m²

Hence

The lift force needs to be balance the weight of aircraft

Hence

Or

samet mamat answered 2 years ago

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