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Final changes to code, sorry it's messy lol

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William Johnstone 2024-11-27 21:42:29 +00:00
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Raymer's Aircraft Calculations (IMPERIAL UNITS)
Weight Estimation (mass): 1.6966 lbs
Typical Weight Area Ratio: 6.0000 lbs/ft²
Main Wing Area: 0.2828 ft²
Lift to Drag Ratio: 5.0000
Aspect Ratio: 13.5523
Main Wing Span 1.9576 ft
Main Wing Chord Length 0.1444 ft
Fuselage Length 1.1084 ft
Tail Positioning (Moment arm location) 0.7205 ft
Vertical Tail Area: 0.0154 ft²
Horizontal Tail Area: 0.0283 ft²
End of imperial numbers (THANK THE LORD!)
Weight Estimation (mass): 0.7696 kg
Total Lift Force: 7.5493 N
BENDING MOMENTS
Wing Span: 0.5967 m
Bending Moment at of 1 Wing from root: 0.5631 Nm
Second moment of inertia for 4mm: 2.1333333333333337e-11 m^4
Max Stress for 4mm spar: 52786068.9659 Pa or 52.7861 MPa
Second moment of inertia for 6mm: 1.08e-10 m^4
Max Stress for 6mm spar: 15640316.7306 Pa or 15.6403 MPa
Second moment of inertia for new test: 8e-12 m^4
Max Stress for new test spar: 70381425.2878 Pa or 70.3814 MPa
Second moment of inertia for 6x3mm: 6.431250000000002e-11 m^4
Max Stress for 6x3mm: 15321126.5933 Pa or 15.3211 MPa
Second moment of inertia for 6x3.5mm: 6.25e-14 m^4
Max Stress for 6x3.5mm: 2252205609.2100 Pa or 2252.2056 MPa
Bending Moment at of 1 Wing from root: 0.5631 Nm
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Everything after this is based on numbers from final CAD model. Thus more relevant
Weight (Final, from CAD Model) (mass): 0.2620 kg
Total Lift Force: 2.5702 N
BENDING MOMENTS (LATEST, THESE ARE THE ONLY ONES RELEVANT)
Wing Span: 0.5967 m
Bending Moment at of 1 Wing from root: 0.1917 Nm
Second moment of inertia for final model: 2.3437500000000006e-11 m^4
Max Stress for final model spar: 10223765.5151 Pa or 10.2238 MPa
Balsa Wood Bending Stress Upper Limit: 21.8564MPa, Lower Limit: 17.5816 MPa
Safety Factor: 1.7 - 2.1