Hello,
Does anybody have knowledge about using aluminum alloy 6005-T5 for a
wing spar extrusion in replacement of 6061-T6 ?
Apparently it has the same properties and is more extrudable. I am
concerned by the "same properties", especially fatigue; but cannot
find anything on the subject and I am completely ignorant myself.
Thanks for any input !
J
ean-Charles

On Feb 22, 9:14 am, "jeanch" > wrote:
> Hello,
> Does anybody have knowledge about using aluminum alloy 6005-T5 for a
> wing spar extrusion in replacement of 6061-T6 ?
> Apparently it has the same properties and is more extrudable. I am
> concerned by the "same properties", especially fatigue; but cannot
> find anything on the subject and I am completely ignorant myself.
> Thanks for any input !
> J
> ean-Charles

>From Matweb.com

6005 T5
Tensile Strength, Ultimate 260 MPa 37700 psi
Tensile Strength, Yield 240 MPa 34800 psi
Elongation at Break 8 % 8 % In 5 cm; Sample 1.6 mm thick
Modulus of Elasticity 69 GPa 10000 ksi Average of Tension and
Compression. In Aluminum alloys, the compressive modulus is typically
2% greater than the tensile modulus
Poisson's Ratio 0.33 0.33 Estimated from trends in similar Al
alloys.
Fatigue Strength 100 MPa 14500 psi 500,000,000 Cycles
Shear Modulus 26 GPa 3770 ksi Estimated from similar Al alloys.
Shear Strength 205 MPa 29700 psi




6061 T6
Ultimate Tensile Strength 310 MPa 45000 psi AA; Typical
Tensile Yield Strength 276 MPa 40000 psi AA; Typical
Elongation at Break 12 % 12 % AA; Typical; 1/16 in. (1.6 mm)
Thickness
Elongation at Break 17 % 17 % AA; Typical; 1/2 in. (12.7 mm)
Diameter
Modulus of Elasticity 68.9 GPa 10000 ksi AA; Typical; Average of
tension and compression. Compression modulus is about 2% greater than
tensile modulus.
Notched Tensile Strength 324 MPa 47000 psi 2.5 cm width x 0.16 cm
thick side-notched specimen, Kt = 17.
Ultimate Bearing Strength 607 MPa 88000 psi Edge distance/pin
diameter = 2.0
Bearing Yield Strength 386 MPa 56000 psi Edge distance/pin diameter =
2.0
Poisson's Ratio 0.33 0.33 Estimated from trends in similar Al
alloys.
Fatigue Strength 96.5 MPa 14000 psi AA; 500,000,000 cycles completely
reversed stress; RR Moore machine/specimen
Fracture Toughness 29 MPa-m½ 26.4 ksi-in½ KIC; TL orientation.
Machinability 50 % 50 % 0-100 Scale of Aluminum Alloys
Shear Modulus 26 GPa 3770 ksi Estimated from similar Al alloys.
Shear Strength 207 MPa 30000 psi AA; Typical

On Feb 22, 11:14 am, "jeanch" > wrote:
> Hello,
> Does anybody have knowledge about using aluminum alloy 6005-T5 for a
> wing spar extrusion in replacement of 6061-T6 ?
> Apparently it has the same properties and is more extrudable. I am
> concerned by the "same properties", especially fatigue; but cannot
> find anything on the subject and I am completely ignorant myself.
> Thanks for any input !
> J
> ean-Charles

Check out www.matweb.com
Search 6005-t5 and 6061-t6
Data sheets for each material are available.
Regarding replacing a wing spar extrusion.......that would be your
call. I have made substitutions in a similar situation eg. wing spar
connectors, but have not flown the ship yet.
Time will tell.
Clark

On Mar 5, 5:31 pm, wrote:
> On Feb 22, 11:14 am, "jeanch" > wrote:
>
> > Hello,
> > Does anybody have knowledge about using aluminum alloy 6005-T5 for a
> > wing spar extrusion in replacement of 6061-T6 ?
> > Apparently it has the same properties and is more extrudable. I am
> > concerned by the "same properties", especially fatigue; but cannot
> > find anything on the subject and I am completely ignorant myself.
> > Thanks for any input !
> > J
> > ean-Charles
>
> Check outwww.matweb.com
> Search 6005-t5 and 6061-t6
> Data sheets for each material are available.
> Regarding replacing a wing spar extrusion.......that would be your
> call. I have made substitutions in a similar situation eg. wing spar
> connectors, but have not flown the ship yet.
> Time will tell.
> Clark



Thanks Clark
But I know now that I wont go this route because I cannot find enough
information.
What is your "ship" ?