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CH10 (smoothed) (ch10sm-il)

CH10 (smoothed) - Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil


Airfoil ch10sm-il
Details Dat file Parser  
(ch10sm-il) CH10 (smoothed)
Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil
Max thickness 12.8% at 30.6% chord.
Max camber 10.2% at 49.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
CH10 (smoothed)
       1.00000     0.00005
       0.99754     0.00169
       0.99070     0.00579
       0.98037     0.01111
       0.96698     0.01721
       0.95044     0.02452
       0.93064     0.03317
       0.90775     0.04292
       0.88202     0.05367
       0.85370     0.06522
       0.82309     0.07725
       0.79048     0.08942
       0.75616     0.10143
       0.72043     0.11298
       0.68359     0.12384
       0.64594     0.13374
       0.60778     0.14243
       0.56937     0.14970
       0.53099     0.15538
       0.49265     0.15942
       0.45435     0.16176
       0.41638     0.16240
       0.37887     0.16133
       0.34204     0.15862
       0.30609     0.15434
       0.27120     0.14859
       0.23760     0.14148
       0.20549     0.13310
       0.17504     0.12355
       0.14648     0.11291
       0.11999     0.10132
       0.09576     0.08896
       0.07395     0.07611
       0.05468     0.06312
       0.03811     0.05032
       0.02433     0.03793
       0.01338     0.02615
       0.00548     0.01531
       0.00098     0.00586
       0.00000     0.00014
       0.00098    -0.00450
       0.00548    -0.00914
       0.01338    -0.01179
       0.02433    -0.01269
       0.03811    -0.01209
       0.05468    -0.01028
       0.07395    -0.00759
       0.09576    -0.00435
       0.11999    -0.00076
       0.14648     0.00320
       0.17504     0.00748
       0.20549     0.01201
       0.23760     0.01667
       0.27120     0.02136
       0.30609     0.02597
       0.34204     0.03040
       0.37887     0.03457
       0.41638     0.03839
       0.45435     0.04178
       0.49265     0.04466
       0.53099     0.04693
       0.56937     0.04851
       0.60778     0.04933
       0.64594     0.04932
       0.68359     0.04845
       0.72043     0.04672
       0.75616     0.04423
       0.79048     0.04108
       0.82309     0.03739
       0.85370     0.03322
       0.88202     0.02867
       0.90775     0.02386
       0.93064     0.01896
       0.95044     0.01410
       0.96698     0.00936
       0.98037     0.00516
       0.99070     0.00212
       0.99754     0.00044
       1.00000    -0.00006
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Polars for CH10 (smoothed) (ch10sm-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ch10sm-il50,00096.2 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ch10sm-il50,000512.4 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ch10sm-il100,000910.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ch10sm-il100,000538.1 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ch10sm-il200,000973.2 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ch10sm-il200,000586.2 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ch10sm-il500,0009135.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ch10sm-il500,0005132.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ch10sm-il1,000,0009175.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ch10sm-il1,000,0005164 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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