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DAE-51 AIRFOIL (dae51-il)

DAE-51 AIRFOIL - Drela DAE51 low Reynolds number airfoil


Airfoil dae51-il
Details Dat file Parser  
(dae51-il) DAE-51 AIRFOIL
Drela DAE51 low Reynolds number airfoil
Max thickness 9.4% at 30.7% chord.
Max camber 4% at 46.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
DAE-51 AIRFOIL
      40.0      41.0

 0.0000000 0.0000000
 0.0041977 0.0095700
 0.0100356 0.0154241
 0.0200350 0.0227665
 0.0348482 0.0311300
 0.0540182 0.0397400
 0.0764527 0.0479203
 0.1011350 0.0553181
 0.1273392 0.0618114
 0.1546283 0.0674128
 0.1826904 0.0721660
 0.2113082 0.0761239
 0.2403358 0.0793401
 0.2696742 0.0818597
 0.2992332 0.0837195
 0.3289599 0.0849515
 0.3588182 0.0855796
 0.3887731 0.0856308
 0.4187877 0.0851351
 0.4488457 0.0841175
 0.4789282 0.0826078
 0.5089862 0.0806341
 0.5389917 0.0782224
 0.5689247 0.0753936
 0.5987790 0.0721627
 0.6285808 0.0685028
 0.6583750 0.0644109
 0.6882508 0.0599010
 0.7182678 0.0550003
 0.7484503 0.0497218
 0.7787921 0.0441214
 0.8092952 0.0382822
 0.8399634 0.0322472
 0.8707898 0.0260833
 0.9016322 0.0199055
 0.9315834 0.0139837
 0.9574376 0.0089976
 0.9758121 0.0055268
 0.9891618 0.0030357
 0.9999979 0.0010000

 0.0000000 0.0000000
 0.0001209 -.0014656
 0.0010059 -.0040753
 0.0027994 -.0064104
 0.0060276 -.0085090
 0.0119707 -.0105878
 0.0227109 -.0126946
 0.0403478 -.0145033
 0.0642490 -.0156413
 0.0918984 -.0160685
 0.1213212 -.0159319
 0.1515756 -.0154033
 0.1822458 -.0145914
 0.2131627 -.0135661
 0.2442524 -.0123857
 0.2754751 -.0110962
 0.3068076 -.0097325
 0.3382381 -.0083288
 0.3697316 -.0069239
 0.4011892 -.0055351
 0.4326007 -.0041804
 0.4639783 -.0028737
 0.4953260 -.0016220
 0.5266438 -.0004364
 0.5579286 0.0006722
 0.5891795 0.0016938
 0.6203865 0.0026153
 0.6515426 0.0034188
 0.6826429 0.0040872
 0.7136883 0.0045996
 0.7446840 0.0049369
 0.7756378 0.0050861
 0.8065398 0.0050393
 0.8373671 0.0047795
 0.8681286 0.0042725
 0.8989804 0.0034777
 0.9298645 0.0023879
 0.9565697 0.0012247
 0.9753916 0.0002834
 0.9889824 -.0004325
 1.0000000 -.0010000
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Lednicer format dat file
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Polars for DAE-51 AIRFOIL (dae51-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   dae51-il50,000939.3 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dae51-il50,000541 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dae51-il100,000962.6 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   dae51-il100,000563.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   dae51-il200,000987.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dae51-il200,000584.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   dae51-il500,0009121.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   dae51-il500,0005110.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   dae51-il1,000,0009144.4 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dae51-il1,000,0005127.2 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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