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DAE-11 AIRFOIL (dae11-il)

DAE-11 AIRFOIL - Drela DAE11 low Reynolds number airfoil


Airfoil dae11-il
Details Dat file Parser  
(dae11-il) DAE-11 AIRFOIL
Drela DAE11 low Reynolds number airfoil
Max thickness 12.8% at 32.8% chord.
Max camber 6.6% at 44.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
DAE-11 AIRFOIL
      42.0      40.0

 0.0000000 0.0000000
 0.0007570 0.0051431
 0.0032916 0.0114678
 0.0082926 0.0193346
 0.0164960 0.0287274
 0.0283640 0.0393002
 0.0439665 0.0505399
 0.0628794 0.0618045
 0.0844076 0.0725648
 0.1079150 0.0825170
 0.1329336 0.0915270
 0.1590953 0.0995398
 0.1861180 0.1065505
 0.2137908 0.1125580
 0.2419395 0.1175854
 0.2704253 0.1216576
 0.2991491 0.1248017
 0.3280559 0.1270426
 0.3570916 0.1283815
 0.3861833 0.1288502
 0.4152550 0.1284338
 0.4442736 0.1271093
 0.4732231 0.1248878
 0.5020466 0.1217780
 0.5306811 0.1177742
 0.5591414 0.1128383
 0.5875807 0.1069073
 0.6162661 0.0999911
 0.6454374 0.0922048
 0.6752228 0.0837204
 0.7056532 0.0747378
 0.7366037 0.0655023
 0.7673512 0.0564167
 0.7977796 0.0476052
 0.8279501 0.0391518
 0.8579515 0.0311284
 0.8879669 0.0235641
 0.9186085 0.0163798
 0.9478748 0.0100446
 0.9700075 0.0056151
 0.9864834 0.0025379
 1.0000000 -.0000000

 0.0000000 0.0000000
 0.0004919 -.0034860
 0.0020116 -.0064284
 0.0044148 -.0087908
 0.0080862 -.0107002
 0.0141149 -.0123747
 0.0245731 -.0138784
 0.0414512 -.0148893
 0.0648951 -.0150664
 0.0926077 -.0144625
 0.1225845 -.0132928
 0.1536785 -.0117470
 0.1853836 -.0099672
 0.2174497 -.0080524
 0.2497389 -.0060686
 0.2821721 -.0040608
 0.3146113 -.0020681
 0.3469645 -.0001193
 0.3792396 0.0017525
 0.4114338 0.0035362
 0.4435539 0.0052000
 0.4756050 0.0067337
 0.5075752 0.0081154
 0.5394692 0.0093041
 0.5713123 0.0102848
 0.6031123 0.0110455
 0.6348824 0.0115701
 0.6666354 0.0118657
 0.6983765 0.0119312
 0.7301015 0.0117728
 0.7617894 0.0113933
 0.7934214 0.0107738
 0.8249984 0.0099002
 0.8565623 0.0087586
 0.8883292 0.0073310
 0.9200152 0.0056143
 0.9479936 0.0038679
 0.9696512 0.0023497
 0.9862833 0.0010768
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for DAE-11 AIRFOIL (dae11-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   dae11-il50,00096.4 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   dae11-il50,000513.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dae11-il100,000931.3 at α=13°Mach=0 Ncrit=9Xfoil predictionDetails
   dae11-il100,000532.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dae11-il200,000979 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dae11-il200,000583.4 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   dae11-il500,0009135.8 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dae11-il500,0005132.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   dae11-il1,000,0009177.3 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dae11-il1,000,0005165 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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