32fordboy
Well-Known Member
I've been messing around with Neal Willford's spreadsheets lately, just trying to learn some new things. They are very cool to experiment with. Quick question, though:
On the S311-AC Design-Tails worksheet, I have a wingspan of 26.4 feet, about 30 inches of that is fuselage (it's a low wing monoplane). I manipulate the wing area to 117 sq ft and that gives me a tip chord of 40 inches or so and a root chord of 66 inches or so, which matches my hypothetical design. However, the design really has 103 sq feet. Is the larger 117 sq ft from the spreadsheet calculating the wing area inside the fuselage? Is there a fix for this, or is it supposed to be this way?
I am trying to figure Flap Delta cl, Flap delta cm, and Flap Alpha 0 estimates, but really can't until I know what's going on here. Maybe I need to subtract the fuselage width from the wingspan and enter that number into the "wingspan" field?
Hopefully I said that in a way that makes any sense, so thanks for any help!
On the S311-AC Design-Tails worksheet, I have a wingspan of 26.4 feet, about 30 inches of that is fuselage (it's a low wing monoplane). I manipulate the wing area to 117 sq ft and that gives me a tip chord of 40 inches or so and a root chord of 66 inches or so, which matches my hypothetical design. However, the design really has 103 sq feet. Is the larger 117 sq ft from the spreadsheet calculating the wing area inside the fuselage? Is there a fix for this, or is it supposed to be this way?
I am trying to figure Flap Delta cl, Flap delta cm, and Flap Alpha 0 estimates, but really can't until I know what's going on here. Maybe I need to subtract the fuselage width from the wingspan and enter that number into the "wingspan" field?
Hopefully I said that in a way that makes any sense, so thanks for any help!
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