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DAE-21 AIRFOIL (dae21-il)

DAE-21 AIRFOIL - Drela DAE21 low Reynolds number airfoil


Airfoil dae21-il
Details Dat file Parser  
(dae21-il) DAE-21 AIRFOIL
Drela DAE21 low Reynolds number airfoil
Max thickness 11.8% at 32% chord.
Max camber 6.6% at 43.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
DAE-21 AIRFOIL
      41.0      40.0

 0.0000000 0.0000000
 0.0019499 0.0094143
 0.0058726 0.0168344
 0.0128414 0.0257007
 0.0235491 0.0358572
 0.0381738 0.0467397
 0.0563235 0.0576674
 0.0773093 0.0681312
 0.1004421 0.0778091
 0.1251679 0.0865420
 0.1510838 0.0942810
 0.1779137 0.1010179
 0.2054597 0.1067869
 0.2335497 0.1116249
 0.2620447 0.1155580
 0.2908337 0.1186110
 0.3198298 0.1208060
 0.3489769 0.1221590
 0.3782181 0.1226940
 0.4075043 0.1224241
 0.4367895 0.1213641
 0.4660367 0.1195231
 0.4952380 0.1169041
 0.5244452 0.1134791
 0.5537366 0.1092231
 0.5831829 0.1041271
 0.6128333 0.0981911
 0.6427197 0.0914251
 0.6728732 0.0838491
 0.7033536 0.0756151
 0.7341761 0.0669101
 0.7652836 0.0579302
 0.7962591 0.0489752
 0.8268646 0.0402772
 0.8571590 0.0319612
 0.8872915 0.0241162
 0.9177019 0.0167402
 0.9476904 0.0100812
 0.9703616 0.0054910
 0.9867118 0.0024176
 1.0000000 -.0000000

 0.0000000 0.0000000
 0.0007544 -.0051560
 0.0021685 -.0080058
 0.0043676 -.0102378
 0.0077967 -.0120597
 0.0136487 -.0135165
 0.0242638 -.0146061
 0.0416670 -.0150185
 0.0659711 -.0144016
 0.0945612 -.0130036
 0.1252703 -.0110646
 0.1569084 -.0088454
 0.1890175 -.0064893
 0.2213756 -.0040902
 0.2537097 -.0017130
 0.2859448 0.0006071
 0.3180979 0.0028502
 0.3501810 0.0049924
 0.3821912 0.0070175
 0.4141243 0.0088996
 0.4459834 0.0106108
 0.4777645 0.0121389
 0.5094687 0.0134480
 0.5411229 0.0145161
 0.5727550 0.0153362
 0.6043642 0.0159113
 0.6359443 0.0162274
 0.6675085 0.0162705
 0.6990697 0.0160426
 0.7306199 0.0155557
 0.7621321 0.0147988
 0.7936034 0.0137559
 0.8250546 0.0124160
 0.8565398 0.0107781
 0.8882250 0.0088442
 0.9200413 0.0066313
 0.9485005 0.0044452
 0.9702268 0.0026420
 0.9865699 0.0012025
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for DAE-21 AIRFOIL (dae21-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   dae21-il50,00097.1 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   dae21-il50,000517.1 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   dae21-il100,000945.9 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   dae21-il100,000550.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dae21-il200,000986.3 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   dae21-il200,000588.7 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   dae21-il500,0009136.5 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dae21-il500,0005130.4 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   dae21-il1,000,0009173.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   dae21-il1,000,0005158.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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