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#All of the data below was derived, but not copied, from the NASA Tech. #Note D-1574.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 # #Fn= 105 # 2014-T6 ALUMINUM, WROUGHT LONGITUDINAL # SMITH ET AL,NASA TN D-1574,1963 # BHN 150/160 # #FileType= strain_life #DataType= raw #TIMEcol= 0 #NAME= AA2014-T6 #NAME= Aluminum #Stress_units= ksi #Strain_units= strain #Su= 74.00 #ksi #Sy= 66.90 #ksi #E= 9993. #ksi #%RA= 25.0 #BHN= 155. #NO. FAT. PTS.= 12 #Tot Strain 2Nf Stress Mean Pl_Strain Initial #_ Amp Amp Stress Amp Elastic Mod. 0.033700 84. 77.45 0. 0.024900 9993. 0.016400 406. 70.92 0. 0.009300 9993. 0.010200 1216. 63.53 0. 0.003800 9993. 0.006800 3220. 58.45 0. 0.001000 9993. 0.006800 3960. 58.45 0. 0.001000 9993. 0.005400 8360. 53.52 0. 0.000100 9993. 0.003600 123400. 35.97 0. 0.000000 9993. 0.004600 191100. 45.98 0. 0.000000 9993. 0.003100 458000. 31.04 0. 0.000000 9993. 0.003300 570000. 33.50 0. 0.000000 9993. 0.002900 788000. 29.01 0. 0.000000 9993. 0.002900 836000. 29.01 0. 0.000000 9993. #Here is the bottom part of the html graph/calc wrapper----------- #