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This page will list a number of tables with relevant Material and Mechanical Properties for you to use in your design and calculations. Please let us know via the 'Add Material or Mechanical Properties' - section in the Discussion Board if you feel there are errors or that you would like to see certain data added. We will endeavour to comply with all requests where possible.

Table 1: Properties of metals and their alloys
Metal Alloy \( E \) \( G \) \( \sigma_y \) \( \sigma_{ult} \) \( \sigma_{ult}/\rho \) \( \epsilon \) \( ν \) \( \rho \) \( L_{ult} \) \( \sqrt{E}/\rho \)
[\( GPa \)] [\( GPa \)] [\( MPa \)] [\( MPa \)] [\(kN \cdot m/kg \)] [\( \% \)] [\( - \)] [\( g/cm^3 \)] [\( km \)] [\( 10^6 \cdot mm^{7/3} N^{2/3} \)]
Steel AISI 301 193 71 965 1257 159 40 0.3 8.00 16.2 0.72
AISI 4340 205 80 470 745 95 22 0.29 7.85
D6AC 210 84 1724 1931 248 7 0.21 7.87 25.0 0.76
Aluminum
AA 2024-T3 72 27 345 483 174 18 0.33 2.78 17.7 1.50
AA 7475-T761 70
27 448
517 184 12 0.33 2.81 18.7 1.47
Titanium Ti6Al-4V (5) 114 44 880 950 214 14 0.34 4.43 21.8 1.09
Magnesium AZ31B-H24 45 17 221 290 163 15 0.35 1.78 16.6 2.00
Table 2: Properties of various composites
Material Fiber Orientation \( E_x \) \( E_y \)
\( \sigma_{U \> x} \) \( \sigma_{U \> y} \)
Note
\( 0^{\circ}  \) \( 45^{\circ} \) \( 90^{\circ} \) [\( kN/mm^2 \)] [\( kN/mm^2 \)] [\( N/mm^2 \)] [\( N/mm^2 \)]
E-Glass epoxy 100% 0% 0% 45 8 1020 40 Unidirectional
0% 0% 100% 8 45 40 1020 Unidirectional
50% 0% 50% ~26 ~26 ~530 ~530 Cross-ply
25% 50% 25% ~20 ~20 ~325 ~325 Quasi-isotropic
High modulus carbon epoxy 100%
0%
0%
220 10 760 40 Unidirectional
Table 3: Coefficients of thermal expansion for various materials
Material
\(  \alpha_x \)
\( \alpha_y \)
[\( 1/ ^{\circ} C \)]
[\( 1/ ^{\circ} C \)]
Titanium Tu-6Al-4V (Grade 5) \( 9.2 \cdot 10^{-6} \) \( 9.2 \cdot 10^{-6} \)
Aluminum 2024-T3 \( 22 \cdot 10^{-6} \) \( 22 \cdot 10^{-6} \)
Magnesium AZ31-H24 \( 26 \cdot 10^{-6} \) \( 26 \cdot 10^{-6} \)
S2-glass epoxy UD-60% \( 26.2 \cdot 10^{-6} \) \( 6.1 \cdot 10^{-6} \)
Carbon epoxy UD-60% \( -0.4 \cdot 10^{-6} \) \(27 \cdot 10^{-6} \)
Table 4: Illustration of typical specific material properties (note: \(\gamma = \rho g\))
Material Specific modulus Column stability Sheet stability
\( E/ \gamma \) \( \% \) \( \sqrt{E}/\gamma \) \( \% \) \( \sqrt[3] {E} / \gamma \)
\( \% \)
Aluminum 2500 108 9.5 62 1.5 52
Steel 2692 100 5.9 100 0.8 100
Spruce 2340 115 22.3 26 4.7 16
Birch 2538 106 19.8 30 3.9 19
Bone 1500 179 9.0 65 1.6 47
Titanium 2622 103 7.8 76 1.1 73
Isotropic carbon composite 3333 81 14.9 40 2.5 32
Isotropic E-glass fibre composite 536 50.2 4.1 116 1.1 73
Isotropic aramid fibre composite 1760 153 11.4 52 2.1 38
Table 5: Comparison of composites and aluminum based on relevant strength values
Material Lay-up \( E \) \( E/ \rho \) \( \sigma_{max} \) \( \sigma_{max} / \rho \) Comment
\( \% 0^{\circ}/ \pm 45^{\circ} / 90^{\circ} \)
\( [GPa] \) \( [MPa \cdot m^3/kg] \) \( [MPa] \) \( [MPa \cdot m^3/kg] \)
CFRP (T800S) 60 / 30 / 10 103 64 360 0.225 Tail plane shells
CFRP (T800S) 40 / 50 / 10 77 48 270 0.170
CFRP ( T800S) 20 / 70 / 10 50 31 175 0.110 Fuselage side shell
2xxx Al-alloy 72 26 440 0.160
7xxx Al-alloy 72 26 565 0.205
Al-Li alloy 77 29 515 0.195
Table 6: Comparison of critical cracks lengths of various aerospace alloys
Alloy \( \sigma_{0.2} \) \( \sigma_{crit} \) \( K_Ic \)
\( a_{crit} \)
[\( MPa \) ]
[\( MPa \)] [\( MPa \sqrt{m} \)]
[\( mm \)]
2024-T3 360 180 40 15.7
7075-T6 470 235 27 4.2
Ti-6Al-4V 1020 510 50 3.1
4340 steel 1600 830 58 1.55