Fatigue Properties of 2024-T42 Clad Sheet
Fatigue Properties of 2024-T42 Clad Sheet
(OP)
Does anyone know of a reference for fatigue data (S-N curves, Goodman diagrams, etc.) for 2024-T42 clad sheet?
Alternately, can anyone comment on the comparitive fatigue performance of 2024-T42 clad sheet and 2024-T3 clad sheet? The static strength is higher but the hardness lower for -T42. Overall, I'm assuming that the fatigue properties of -T42 are lesser as -T3 is much more commonly used for fatigue critical applications.
Alternately, can anyone comment on the comparitive fatigue performance of 2024-T42 clad sheet and 2024-T3 clad sheet? The static strength is higher but the hardness lower for -T42. Overall, I'm assuming that the fatigue properties of -T42 are lesser as -T3 is much more commonly used for fatigue critical applications.





RE: Fatigue Properties of 2024-T42 Clad Sheet
RE: Fatigue Properties of 2024-T42 Clad Sheet
Need look no further than Mil-Hdbk-5 and/or MMPDS.
You can carry out some simple comparative fatigue checks for each material and see the differences.
When i visualise fatigue comparisons by eye, i always think that bendy/flexible materials are better than stiff materials. Just the way i think about it.
What application are you going to use the materials in?
RE: Fatigue Properties of 2024-T42 Clad Sheet
Naturally MMPDS was the first place I looked but the T4 curves are for thicker stock than sheet and the curves for T3 are all sheet...
My understanding is that thickness is a factor in fracture toughness...so would there really be a basis of comparison?
Flexible materials better in fatigue...yes. I don't disagree with what you are saying and I can see how your experience may bouy your confidence, but for myself, I think I'll need a bit more information/understanding before
proceeding to presentation, approval, and installation based on this loose method.
The material is an existing aircraft pressurized skin.
RE: Fatigue Properties of 2024-T42 Clad Sheet
RE: Fatigue Properties of 2024-T42 Clad Sheet
If your talking about aircraft pressure skins, the skin and frames carry the hoop tension loads in about an 80-85%/15-20% proportions. Depending on the aircraft type?? You would end up with anwhere between 10-18Ksi hoop tension.
But the fatigue requirements of each aircraft type should be defined by the oem.