piper cherokee wing area is 16m², span is 9.75m. total
weight is 1100kg. airfoil is NACA...
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Mechanical Engineering
piper cherokee wing area is 16m², span is 9.75m. totalweight is 1100kg. airfoil is NACA 65-415 and lift coefficient slopeis 0.1033 per degree. αL=0 is -1.5degree. Assume τ = 0.12. when airdensity is 1.23Kg/m³ and speed is 193Km/h. Determine the wing'sangle of attack
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4.3 Ratings (671 Votes)
Let the angle of attack be degreesThe lift
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