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S8035 for RC aerobatic 14% thick (s8035-il)

S8035 for RC aerobatic 14% thick - Selig S8035 low Reynolds number airfoil


Airfoil s8035-il
Details Dat file Parser  
(s8035-il) S8035 for RC aerobatic 14% thick
Selig S8035 low Reynolds number airfoil
Max thickness 14% at 29.1% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  S8035 for RC aerobatic  14% thick
       1.00000     0.00000
       0.99899     0.00005
       0.99604     0.00033
       0.99135     0.00097
       0.98510     0.00198
       0.97745     0.00329
       0.96848     0.00476
       0.95817     0.00629
       0.94646     0.00786
       0.93335     0.00955
       0.91891     0.01137
       0.90320     0.01332
       0.88626     0.01543
       0.86817     0.01770
       0.84901     0.02015
       0.82890     0.02276
       0.80791     0.02550
       0.78613     0.02833
       0.76361     0.03123
       0.74042     0.03418
       0.71664     0.03717
       0.69236     0.04015
       0.66764     0.04310
       0.64253     0.04601
       0.61713     0.04886
       0.59152     0.05161
       0.56575     0.05423
       0.53988     0.05671
       0.51400     0.05905
       0.48818     0.06120
       0.46248     0.06315
       0.43694     0.06488
       0.41165     0.06640
       0.38669     0.06767
       0.36210     0.06867
       0.33792     0.06939
       0.31423     0.06985
       0.29111     0.07002
       0.26858     0.06986
       0.24668     0.06940
       0.22548     0.06865
       0.20504     0.06758
       0.18539     0.06617
       0.16655     0.06445
       0.14856     0.06243
       0.13150     0.06012
       0.11537     0.05748
       0.10018     0.05456
       0.08598     0.05138
       0.07283     0.04794
       0.06072     0.04423
       0.04964     0.04028
       0.03961     0.03615
       0.03071     0.03186
       0.02292     0.02739
       0.01620     0.02279
       0.01057     0.01814
       0.00613     0.01352
       0.00288     0.00888
       0.00077     0.00428
       0.00000     0.00000
       0.00077    -0.00428
       0.00288    -0.00888
       0.00613    -0.01352
       0.01057    -0.01814
       0.01620    -0.02279
       0.02292    -0.02739
       0.03071    -0.03186
       0.03961    -0.03615
       0.04964    -0.04028
       0.06072    -0.04423
       0.07283    -0.04794
       0.08598    -0.05138
       0.10018    -0.05456
       0.11537    -0.05748
       0.13150    -0.06012
       0.14856    -0.06243
       0.16655    -0.06445
       0.18539    -0.06617
       0.20504    -0.06758
       0.22548    -0.06865
       0.24668    -0.06940
       0.26858    -0.06986
       0.29111    -0.07002
       0.31423    -0.06985
       0.33792    -0.06939
       0.36210    -0.06867
       0.38669    -0.06767
       0.41165    -0.06640
       0.43694    -0.06488
       0.46248    -0.06315
       0.48818    -0.06120
       0.51400    -0.05905
       0.53988    -0.05671
       0.56575    -0.05423
       0.59152    -0.05161
       0.61713    -0.04886
       0.64253    -0.04601
       0.66764    -0.04310
       0.69236    -0.04015
       0.71664    -0.03717
       0.74042    -0.03418
       0.76361    -0.03123
       0.78613    -0.02833
       0.80791    -0.02550
       0.82890    -0.02276
       0.84901    -0.02015
       0.86817    -0.01770
       0.88626    -0.01543
       0.90320    -0.01332
       0.91891    -0.01137
       0.93335    -0.00955
       0.94646    -0.00786
       0.95817    -0.00629
       0.96848    -0.00476
       0.97745    -0.00329
       0.98510    -0.00198
       0.99135    -0.00097
       0.99604    -0.00033
       0.99899    -0.00005
       1.00000     0.00000
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Polars for S8035 for RC aerobatic 14% thick (s8035-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s8035-il50,000924.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s8035-il50,000527.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s8035-il100,000938.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s8035-il100,000539.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   s8035-il200,000952 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s8035-il200,000551.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s8035-il500,000970.6 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8035-il500,000566.9 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8035-il1,000,000983.7 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s8035-il1,000,000578.7 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
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