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I am working on a 3.2 meter wing span electric aircraft with another group of 30 engineering students. In calculating the induced drag and lift for preliminary calcs I am a little confused as to whether I need to include the width of the fuselage in the wing span(b) for induced drag calculation(CL^2/(pi*AR*e) and the area used for the lift calculation. e is assumed to be 0.99 due to taper. Or do I ignore the fuselage contribution and just use the wing area?

thank you!

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# Aerospace Aspect ratio used in induced drag and lift calculation

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