This is my Wing Project with the follow specs
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Wing Area: 1,182m^2
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Wing span: 3,430 m
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Aspect Ratio: 10
*Oswald factor e: 0,76
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Weight (Lift expectet— L=W): 323.73 N
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Speed : starting point is 25m/s…but the wing has leading edge Sweep angle Λ=4,5deg. (V=V0cosΛ=24,92m/s)
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at ρ=1,225kg/m^2
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NACA 4412 (zero Lift cd=0,01638 from airfoiltools.com at Re: 200.000)
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AoA=4
If i use the Total Drag equation :
The Parasitic Drag = 10,60 N and the induced Drag=9,83 N, so the total Drag is: 20,23N
But via the simulation bellow, i get Drag = 11,15N