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Composite Wing Calculator

The document presents a wing bending model detailing various wing properties, loads, moment of area calculations, and material properties. It includes specific measurements for deflection, stress, and shear loads, as well as the structural design of the wing's skin and spar layup. Additionally, it references external resources for material properties and airfoil details.

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John Longbeard
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26 views4 pages

Composite Wing Calculator

The document presents a wing bending model detailing various wing properties, loads, moment of area calculations, and material properties. It includes specific measurements for deflection, stress, and shear loads, as well as the structural design of the wing's skin and spar layup. Additionally, it references external resources for material properties and airfoil details.

Uploaded by

John Longbeard
Copyright
© © All Rights Reserved
We take content rights seriously. If you suspect this is your content, claim it here.
Available Formats
Download as XLSX, PDF, TXT or read online on Scribd
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Wing Bending Model

Wing Properties Wing Load


L: 0.7 m Cl: 2
W: 0.3 m Vmax: 250
T: 0.05 m Load: 1240.5960648
Strut Gap: 0.3 m Load: 126.59143519
Overhang: 0.2 m Load dist: 1772.2800926

Moment of Area Calculations Material Properties


Outer MoA: 1.840777E-06 m^4 E (Cf): 45
Inner MoA: 1.493384E-06 m^4 Layer Thick: 1.6
Total MoA: 3.473934E-07 m^4 Max Stress: 350

Free End Max Deflection Stress at Support


Deflection: 0.191757303 [mm] Stress: 3.6

Centre of struts max deflection Stress at Centre


Deflection: 4.4307E-08 [mm] Stress: -4.6

Unsupported Deflection Between Spars Reaction Loads (Supports)


Span Dist: 0.135 m Load: 620
Skin MoA: 2.389333E-10 m^4 Load: 63
Load: 558 N Fwd Bolt: 482
Deflection (max): 1.663 mm Rear Bolt: 138

Shear Loads (Max, Magnitude)


Outboard: 354
Inboard: 266
Maximum: 354
Spar Thicknesses: 2.1
Shear Stress 0.01
This model simplifies a wing construction into a hollow oval section. Supported and loade
The layup for the skin is alternating layers of 0/90 and 45/45 to create a qusai-orthentrop
Load
[non-dim] Spar locations at 15% and 60% chord. Spar layup should be 45/45 for every layer to the re
km/h Assumed that the centre for lift occurs at 25% chord
N
Kg Materials properties: http://www.performance-composites.com/carbonfibre/mechanical
N/m

Properties
Gpa
mm
Mpa

Support
Mpa

t Centre
Mpa

ds (Supports)
N
Kg
N
N

ax, Magnitude)
N
N
N
mm
Mpa
tion. Supported and loaded as indicated below.
create a qusai-orthentropic skin.

45 for every layer to the required thickness

m/carbonfibre/mechanicalproperties_2.asp
http://airfoiltools.com/airfoil/details?airfoil=e423-il#polars <----- this one

http://airfoiltools.com/airfoil/details?airfoil=e216-il#polars

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