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A18 (smoothed) (a18sm-il)

A18 (smoothed) - Archer A18 F1C free flight airfoil (smoothed)


Airfoil a18sm-il
Details Dat file Parser  
(a18sm-il) A18 (smoothed)
Archer A18 F1C free flight airfoil (smoothed)
Max thickness 7.3% at 27.1% chord.
Max camber 3.8% at 49.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
A18 (smoothed)
       1.00000     0.00307
       0.99754     0.00365
       0.99070     0.00530
       0.98037     0.00771
       0.96698     0.01070
       0.95044     0.01421
       0.93064     0.01819
       0.90775     0.02253
       0.88202     0.02712
       0.85370     0.03185
       0.82309     0.03661
       0.79048     0.04132
       0.75616     0.04591
       0.72043     0.05029
       0.68359     0.05440
       0.64594     0.05819
       0.60778     0.06160
       0.56937     0.06458
       0.53099     0.06710
       0.49265     0.06911
       0.45435     0.07058
       0.41638     0.07143
       0.37887     0.07157
       0.34204     0.07094
       0.30609     0.06951
       0.27120     0.06733
       0.23760     0.06451
       0.20549     0.06114
       0.17504     0.05734
       0.14648     0.05315
       0.11999     0.04860
       0.09576     0.04368
       0.07395     0.03839
       0.05468     0.03277
       0.03811     0.02694
       0.02433     0.02103
       0.01338     0.01513
       0.00548     0.00932
       0.00098     0.00376
       0.00000     0.00000
       0.00098    -0.00348
       0.00548    -0.00770
       0.01338    -0.01118
       0.02433    -0.01388
       0.03811    -0.01581
       0.05468    -0.01699
       0.07395    -0.01740
       0.09576    -0.01708
       0.11999    -0.01611
       0.14648    -0.01461
       0.17504    -0.01269
       0.20549    -0.01047
       0.23760    -0.00805
       0.27120    -0.00550
       0.30609    -0.00290
       0.34204    -0.00033
       0.37887     0.00209
       0.41638     0.00429
       0.45435     0.00617
       0.49265     0.00773
       0.53099     0.00895
       0.56937     0.00984
       0.60778     0.01042
       0.64594     0.01067
       0.68359     0.01060
       0.72043     0.01022
       0.75616     0.00954
       0.79048     0.00858
       0.82309     0.00738
       0.85370     0.00600
       0.88202     0.00450
       0.90775     0.00297
       0.93064     0.00149
       0.95044     0.00015
       0.96698    -0.00098
       0.98037    -0.00187
       0.99070    -0.00252
       0.99754    -0.00292
       1.00000    -0.00306
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Polars for A18 (smoothed) (a18sm-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   a18sm-il50,000944.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   a18sm-il50,000544.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   a18sm-il100,000965.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   a18sm-il100,000563.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   a18sm-il200,000987 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   a18sm-il200,000581.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   a18sm-il500,0009114.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   a18sm-il500,0005102.7 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   a18sm-il1,000,0009132.8 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   a18sm-il1,000,0005116 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
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