# #All of the data below was derived, but not copied, from the NASA Tech. #Note D-7532.The derivations and additions have been made by the members #of the FD+E committee of the SAE. Thus: # #Copyright (C) 2003 Fatigue Design + Evaluation Committee of the SAE. #This data file is free software; you can redistribute it and/or modify #it under the terms of the GNU General Public License as published by #the Free Software Foundation; either version 2 of the license, or (at #your option) any later version. #This data file is distributed in the hope that it will be useful, but #WITHOUT ANY WARRANTY; without even the implied warranty of MERCHANTA- #BILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU General Public #License for more details. #You should have received a copy of the GNU General PUblic License along #with this program; if not, write to the Free Software Foundation, Inc., #59 Temple Place - Suite 330, Boston, MA 02111-1307, USA. Try also their #web site: http://www.gnu.org/copyleft/gpl.html # # AA 2014-T6 ALUMINUM, LONGITUDINAL # NACHTIGALL, NASA TN D-7532,FEB74 # ASSUMED BHN 135 # #FileType= strain_life #DataType= raw #Fn= 160 #TIMEcol= 0 #NAME= Aluminum #NAME= AA2014-T6 #Stress_units= ksi #Strain_units= strain #Su= 77.50 #ksi #Sy= 70.40 #ksi #E= 10791. #ksi #%RA= 0.0 #BHN= 135. #NO. FAT. PTS.= 9 #Tot Strain 2Nf Stress Mean Pl. Strain Initial #_ Amp Amp Stress Amp Elastic Mod. 0.042850 22. 85.86 0. 0.034900 10791. 0.022750 80. 83.69 0. 0.015000 10791. 0.014650 224. 80.06 0. 0.007250 10791. 0.014650 230. 80.21 0. 0.007200 10791. 0.011550 460. 77.31 0. 0.004400 10791. 0.008400 1330. 73.24 0. 0.001700 10791. 0.005050 33040. 54.39 0. 0.000000 10791. 0.003750 148120. 47.57 0. 0.000000 10791. 0.003600 154400. 38.58 0. 0.000000 10791. #Here is the bottom part of the html graph/calc wrapper----------- # #