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S8052 (11.88%) (s8052-il)

S8052 (11.88%) - Selig S8052 low Reynolds number airfoil


Airfoil s8052-il
Details Dat file Parser  
(s8052-il) S8052 (11.88%)
Selig S8052 low Reynolds number airfoil
Max thickness 11.9% at 33.3% chord.
Max camber 1.2% at 44.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S8052 (11.88%)
       1.00000     0.00000
       0.99803     0.00018
       0.99231     0.00079
       0.98301     0.00181
       0.97022     0.00330
       0.95412     0.00533
       0.93491     0.00790
       0.91280     0.01104
       0.88804     0.01472
       0.86087     0.01891
       0.83155     0.02357
       0.80036     0.02863
       0.76759     0.03400
       0.73351     0.03957
       0.69841     0.04524
       0.66259     0.05083
       0.62635     0.05617
       0.58984     0.06088
       0.55299     0.06482
       0.51588     0.06814
       0.47873     0.07081
       0.44169     0.07283
       0.40501     0.07423
       0.36887     0.07498
       0.33344     0.07511
       0.29896     0.07461
       0.26560     0.07351
       0.23357     0.07182
       0.20304     0.06957
       0.17422     0.06676
       0.14727     0.06341
       0.12234     0.05951
       0.09956     0.05510
       0.07907     0.05012
       0.06085     0.04458
       0.04493     0.03864
       0.03140     0.03234
       0.02025     0.02579
       0.01165     0.01916
       0.00552     0.01240
       0.00163     0.00569
       0.00001    -0.00037
       0.00147    -0.00540
       0.00651    -0.00985
       0.01471    -0.01427
       0.02583    -0.01860
       0.03977    -0.02271
       0.05642    -0.02654
       0.07569    -0.03003
       0.09749    -0.03316
       0.12169    -0.03590
       0.14818    -0.03824
       0.17678    -0.04018
       0.20735    -0.04171
       0.23970    -0.04283
       0.27364    -0.04354
       0.30896    -0.04385
       0.34545    -0.04377
       0.38288    -0.04331
       0.42100    -0.04248
       0.45957    -0.04127
       0.49834    -0.03967
       0.53702    -0.03758
       0.57556    -0.03494
       0.61389    -0.03185
       0.65181    -0.02843
       0.68916    -0.02481
       0.72568    -0.02116
       0.76113    -0.01762
       0.79518    -0.01433
       0.82751    -0.01136
       0.85782    -0.00876
       0.88581    -0.00656
       0.91121    -0.00475
       0.93377    -0.00330
       0.95325    -0.00218
       0.96950    -0.00128
       0.98246    -0.00056
       0.99204    -0.00011
       0.99798     0.00002
       1.00000     0.00000
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Polars for S8052 (11.88%) (s8052-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s8052-il50,000931 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8052-il50,000532.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s8052-il100,000948.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8052-il100,000546.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8052-il200,000966.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s8052-il200,000558.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s8052-il500,000981.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8052-il500,000573.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s8052-il1,000,000992.3 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s8052-il1,000,000587.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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