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S8064 (s8064-il)

S8064 - Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF.


Airfoil s8064-il
Details Dat file Parser  
(s8064-il) S8064
Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF.
Max thickness 12.3% at 37.8% chord.
Max camber 1.1% at 56.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S8064
     1.000000    0.000000
     0.997927    0.000125
     0.991844    0.000661
     0.981950    0.001759
     0.968438    0.003565
     0.951588    0.006193
     0.931716    0.009686
     0.909164    0.014035
     0.884293    0.019168
     0.857469    0.024954
     0.829053    0.031198
     0.799390    0.037630
     0.768826    0.043760
     0.737098    0.049161
     0.703928    0.053909
     0.669588    0.058180
     0.634301    0.061961
     0.598271    0.065229
     0.561701    0.067947
     0.524799    0.070079
     0.487769    0.071601
     0.450799    0.072500
     0.414069    0.072755
     0.377770    0.072374
     0.342087    0.071387
     0.307218    0.069831
     0.273369    0.067736
     0.240738    0.065134
     0.209521    0.062054
     0.179900    0.058531
     0.152050    0.054600
     0.126136    0.050302
     0.102312    0.045678
     0.080718    0.040772
     0.061481    0.035636
     0.044723    0.030322
     0.030576    0.024873
     0.019091    0.019310
     0.010271    0.013670
     0.004145    0.008047
     0.000637    0.002692
     0.000328   -0.001911
     0.003568   -0.006325
     0.009851   -0.011082
     0.018933   -0.015812
     0.030792   -0.020402
     0.045404   -0.024768
     0.062686   -0.028860
     0.082555   -0.032657
     0.104908   -0.036143
     0.129620   -0.039299
     0.156536   -0.042118
     0.185485   -0.044585
     0.216282   -0.046683
     0.248732   -0.048388
     0.282633   -0.049680
     0.317775   -0.050530
     0.353959   -0.050905
     0.390991   -0.050795
     0.428663   -0.050184
     0.466779   -0.049071
     0.505162   -0.047491
     0.543597   -0.045496
     0.581815   -0.043133
     0.619551   -0.040409
     0.656518   -0.037280
     0.692670   -0.033539
     0.728117   -0.029328
     0.762681   -0.025064
     0.796024   -0.020943
     0.827817   -0.017097
     0.857738   -0.013617
     0.885475   -0.010558
     0.910730   -0.007944
     0.933228   -0.005769
     0.952715   -0.003991
     0.969006   -0.002502
     0.982067   -0.001257
     0.991810   -0.000404
     0.997911   -0.000042
     1.000000    0.000000
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Polars for S8064 (s8064-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s8064-il50,000931 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s8064-il50,000529.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8064-il100,000948.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s8064-il100,000546.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8064-il200,000968.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8064-il200,000555.2 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s8064-il500,000980.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8064-il500,000565.4 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8064-il1,000,000990 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s8064-il1,000,000570.3 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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