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S8025 (8%) (s8025-il)

S8025 (8%) - Selig S8025 low Reynolds number airfoil


Airfoil s8025-il
Details Dat file Parser  
(s8025-il) S8025 (8%)
Selig S8025 low Reynolds number airfoil
Max thickness 8% at 22.9% chord.
Max camber 0.4% at 18.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S8025 (8%)
       1.00000     0.00000
       0.99919     0.00002
       0.99678     0.00012
       0.99284     0.00034
       0.98745     0.00066
       0.98063     0.00104
       0.97238     0.00147
       0.96270     0.00196
       0.95165     0.00253
       0.93925     0.00318
       0.92556     0.00391
       0.91060     0.00473
       0.89445     0.00563
       0.87713     0.00662
       0.85872     0.00769
       0.83927     0.00885
       0.81884     0.01009
       0.79749     0.01141
       0.77528     0.01281
       0.75230     0.01429
       0.72860     0.01585
       0.70427     0.01749
       0.67938     0.01921
       0.65405     0.02100
       0.62835     0.02284
       0.60235     0.02471
       0.57615     0.02658
       0.54980     0.02845
       0.52339     0.03031
       0.49702     0.03212
       0.47073     0.03387
       0.44461     0.03555
       0.41873     0.03714
       0.39318     0.03862
       0.36801     0.03997
       0.34327     0.04118
       0.31906     0.04223
       0.29543     0.04311
       0.27244     0.04379
       0.25013     0.04426
       0.22857     0.04452
       0.20782     0.04454
       0.18791     0.04428
       0.16884     0.04377
       0.15069     0.04301
       0.13350     0.04199
       0.11729     0.04067
       0.10203     0.03908
       0.08779     0.03725
       0.07462     0.03516
       0.06250     0.03280
       0.05141     0.03021
       0.04137     0.02743
       0.03244     0.02448
       0.02461     0.02134
       0.01781     0.01806
       0.01210     0.01472
       0.00752     0.01136
       0.00406     0.00796
       0.00163     0.00458
       0.00025     0.00141
       0.00020    -0.00126
       0.00177    -0.00376
       0.00481    -0.00649
       0.00907    -0.00932
       0.01451    -0.01216
       0.02109    -0.01496
       0.02877    -0.01763
       0.03761    -0.02012
       0.04765    -0.02244
       0.05882    -0.02462
       0.07109    -0.02660
       0.08447    -0.02836
       0.09896    -0.02993
       0.11451    -0.03130
       0.13107    -0.03247
       0.14862    -0.03343
       0.16716    -0.03417
       0.18662    -0.03474
       0.20694    -0.03511
       0.22809    -0.03530
       0.25002    -0.03530
       0.27267    -0.03515
       0.29596    -0.03483
       0.31986    -0.03436
       0.34431    -0.03374
       0.36923    -0.03299
       0.39455    -0.03211
       0.42021    -0.03112
       0.44614    -0.03002
       0.47227    -0.02883
       0.49851    -0.02754
       0.52481    -0.02615
       0.55113    -0.02470
       0.57738    -0.02320
       0.60349    -0.02168
       0.62936    -0.02015
       0.65494    -0.01862
       0.68013    -0.01712
       0.70485    -0.01564
       0.72904    -0.01420
       0.75261    -0.01281
       0.77549    -0.01147
       0.79761    -0.01020
       0.81890    -0.00899
       0.83929    -0.00786
       0.85871    -0.00681
       0.87710    -0.00583
       0.89441    -0.00494
       0.91057    -0.00413
       0.92552    -0.00340
       0.93922    -0.00276
       0.95163    -0.00219
       0.96269    -0.00170
       0.97237    -0.00127
       0.98062    -0.00090
       0.98745    -0.00057
       0.99284    -0.00029
       0.99677    -0.00010
       0.99919    -0.00001
       1.00000     0.00000
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Polars for S8025 (8%) (s8025-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s8025-il50,000922.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s8025-il50,000526.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s8025-il100,000933.6 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8025-il100,000537.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s8025-il200,000946.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s8025-il200,000548.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8025-il500,000965.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s8025-il500,000565.1 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   s8025-il1,000,000979.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8025-il1,000,000578 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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