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cr001sm (cr001sm-il)

cr001sm - Cody Robertson CR 001 R/C hand-launch low Reynolds number airfoil (smoothed)


Airfoil cr001sm-il
Details Dat file Parser  
(cr001sm-il) cr001sm
Cody Robertson CR 001 R/C hand-launch low Reynolds number airfoil (smoothed)
Max thickness 7.3% at 27.1% chord.
Max camber 4.1% at 45.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
cr001sm
  1.00000 -0.00001
  0.99754  0.00091
  0.99070  0.00289
  0.98037  0.00531
  0.96698  0.00833
  0.95044  0.01199
  0.93064  0.01619
  0.90775  0.02074
  0.88202  0.02558
  0.85370  0.03061
  0.82309  0.03573
  0.79048  0.04085
  0.75616  0.04586
  0.72043  0.05066
  0.68359  0.05518
  0.64594  0.05935
  0.60778  0.06310
  0.56937  0.06639
  0.53099  0.06918
  0.49265  0.07145
  0.45435  0.07317
  0.41638  0.07429
  0.37887  0.07477
  0.34204  0.07456
  0.30609  0.07364
  0.27120  0.07200
  0.23760  0.06968
  0.20549  0.06673
  0.17504  0.06318
  0.14648  0.05904
  0.11999  0.05431
  0.09576  0.04900
  0.07395  0.04314
  0.05468  0.03682
  0.03811  0.03018
  0.02433  0.02336
  0.01338  0.01648
  0.00548  0.00980
  0.00098  0.00373
       0.00000    -0.00008
       0.00098    -0.00330
       0.00548    -0.00651
       0.01338    -0.00827
       0.02433    -0.00929
       0.03811    -0.00989
       0.05468    -0.01015
       0.07395    -0.01007
       0.09576    -0.00965
       0.11999    -0.00891
       0.14648    -0.00788
       0.17504    -0.00656
       0.20549    -0.00499
       0.23760    -0.00323
       0.27120    -0.00133
       0.30609     0.00064
       0.34204     0.00261
       0.37887     0.00453
       0.41638     0.00635
       0.45435     0.00800
       0.49265     0.00948
       0.53099     0.01074
       0.56937     0.01176
       0.60778     0.01250
       0.64594     0.01295
       0.68359     0.01311
       0.72043     0.01296
       0.75616     0.01249
       0.79048     0.01172
       0.82309     0.01068
       0.85370     0.00941
       0.88202     0.00797
       0.90775     0.00643
       0.93064     0.00490
       0.95044     0.00348
       0.96698     0.00226
       0.98037     0.00129
       0.99070     0.00058
       0.99754     0.00014
       1.00000    -0.00002
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Polars for cr001sm (cr001sm-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   cr001sm-il50,000941.2 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   cr001sm-il50,000544.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   cr001sm-il100,000964.8 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   cr001sm-il100,000564.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   cr001sm-il200,000989.3 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   cr001sm-il200,000583.3 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   cr001sm-il500,0009120.2 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   cr001sm-il500,0005105.2 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   cr001sm-il1,000,0009139.9 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   cr001sm-il1,000,0005119.7 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
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