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S1012 (s1012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S1012 (s1012-il)
Reynolds number: 100,000
Max Cl/Cd: 31.12 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1012-il-100000-n5.txt
Download as CSV file: xf-s1012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1012                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8402   0.08205   0.07636  -0.0381   1.0000   0.0423
 -13.750  -0.8804   0.07207   0.06615  -0.0446   1.0000   0.0420
 -13.500  -0.9114   0.06510   0.05894  -0.0479   1.0000   0.0419
 -13.250  -0.9392   0.05951   0.05306  -0.0491   1.0000   0.0422
 -13.000  -0.9605   0.05510   0.04834  -0.0490   1.0000   0.0425
 -12.750  -0.9772   0.05142   0.04437  -0.0479   1.0000   0.0430
 -12.500  -0.9750   0.04947   0.04239  -0.0469   1.0000   0.0438
 -12.250  -0.9745   0.04754   0.04038  -0.0456   1.0000   0.0447
 -12.000  -0.9748   0.04557   0.03827  -0.0440   1.0000   0.0456
 -11.750  -0.9748   0.04360   0.03611  -0.0421   1.0000   0.0467
 -11.500  -0.9742   0.04167   0.03397  -0.0399   1.0000   0.0481
 -11.250  -0.9730   0.03975   0.03173  -0.0374   1.0000   0.0498
 -11.000  -0.9697   0.03789   0.02954  -0.0349   1.0000   0.0516
 -10.750  -0.9577   0.03672   0.02840  -0.0335   1.0000   0.0533
 -10.500  -0.9459   0.03561   0.02723  -0.0319   1.0000   0.0552
 -10.250  -0.9338   0.03436   0.02581  -0.0302   1.0000   0.0576
 -10.000  -0.9215   0.03302   0.02418  -0.0284   1.0000   0.0605
  -9.750  -0.9076   0.03185   0.02295  -0.0269   1.0000   0.0629
  -9.500  -0.8952   0.03101   0.02210  -0.0249   1.0000   0.0653
  -9.250  -0.8850   0.03022   0.02122  -0.0225   1.0000   0.0682
  -9.000  -0.8768   0.02943   0.02024  -0.0195   1.0000   0.0712
  -8.750  -0.8701   0.02866   0.01940  -0.0163   1.0000   0.0738
  -8.500  -0.8646   0.02809   0.01884  -0.0129   1.0000   0.0762
  -8.250  -0.8528   0.02746   0.01812  -0.0106   0.9989   0.0797
  -8.000  -0.8256   0.02659   0.01703  -0.0111   0.9946   0.0849
  -7.750  -0.8007   0.02573   0.01621  -0.0114   0.9903   0.0892
  -7.500  -0.7742   0.02503   0.01540  -0.0118   0.9864   0.0952
  -7.250  -0.7464   0.02424   0.01457  -0.0125   0.9832   0.1010
  -7.000  -0.7210   0.02361   0.01390  -0.0127   0.9791   0.1074
  -6.750  -0.6951   0.02296   0.01320  -0.0128   0.9753   0.1144
  -6.500  -0.6682   0.02239   0.01259  -0.0133   0.9723   0.1224
  -6.250  -0.6405   0.02178   0.01200  -0.0138   0.9699   0.1310
  -6.000  -0.6187   0.02135   0.01150  -0.0131   0.9659   0.1407
  -5.750  -0.5956   0.02083   0.01105  -0.0128   0.9625   0.1511
  -5.500  -0.5694   0.02033   0.01058  -0.0130   0.9595   0.1643
  -5.250  -0.5414   0.01985   0.01016  -0.0135   0.9571   0.1804
  -5.000  -0.5183   0.01944   0.00980  -0.0131   0.9540   0.1986
  -4.750  -0.4989   0.01905   0.00950  -0.0119   0.9502   0.2202
  -4.250  -0.4522   0.01811   0.00894  -0.0111   0.9444   0.2922
  -4.000  -0.4283   0.01753   0.00869  -0.0109   0.9419   0.3536
  -3.750  -0.4160   0.01699   0.00853  -0.0083   0.9380   0.4281
  -3.500  -0.4028   0.01645   0.00858  -0.0054   0.9339   0.5337
  -3.250  -0.3715   0.01686   0.00966  -0.0042   0.9325   0.6586
  -3.000  -0.3462   0.01725   0.01004  -0.0031   0.9299   0.7160
  -2.750  -0.3221   0.01746   0.01017  -0.0021   0.9272   0.7484
  -2.500  -0.3045   0.01771   0.01035   0.0001   0.9233   0.7707
  -2.000  -0.2601   0.01832   0.01085   0.0032   0.9161   0.8036
  -1.750  -0.2324   0.01861   0.01109   0.0037   0.9136   0.8179
  -1.500  -0.2010   0.01892   0.01135   0.0036   0.9115   0.8311
  -1.250  -0.1711   0.01932   0.01174   0.0039   0.9087   0.8428
  -1.000  -0.1445   0.01974   0.01216   0.0049   0.9049   0.8567
  -0.750  -0.1065   0.02020   0.01261   0.0039   0.9026   0.8709
  -0.500  -0.0720   0.02042   0.01282   0.0030   0.8997   0.8818
  -0.250  -0.0274   0.02055   0.01293   0.0000   0.8977   0.8866
   0.000  -0.0001   0.02055   0.01292   0.0000   0.8931   0.8932
   0.250   0.0275   0.02055   0.01293   0.0000   0.8866   0.8977
   0.500   0.0720   0.02042   0.01282  -0.0030   0.8818   0.8997
   0.750   0.1068   0.02019   0.01260  -0.0039   0.8707   0.9026
   1.000   0.1445   0.01974   0.01215  -0.0049   0.8567   0.9049
   1.250   0.1710   0.01932   0.01174  -0.0039   0.8426   0.9088
   1.500   0.2008   0.01892   0.01135  -0.0035   0.8308   0.9115
   1.750   0.2325   0.01860   0.01108  -0.0037   0.8178   0.9136
   2.000   0.2601   0.01832   0.01085  -0.0032   0.8035   0.9161
   2.250   0.2852   0.01802   0.01060  -0.0022   0.7879   0.9193
   2.500   0.3045   0.01772   0.01035  -0.0001   0.7708   0.9233
   2.750   0.3223   0.01746   0.01017   0.0021   0.7487   0.9272
   3.000   0.3462   0.01724   0.01004   0.0030   0.7159   0.9299
   3.250   0.3714   0.01686   0.00967   0.0042   0.6595   0.9325
   3.500   0.4029   0.01644   0.00858   0.0054   0.5347   0.9339
   3.750   0.4159   0.01699   0.00852   0.0083   0.4280   0.9380
   4.000   0.4283   0.01753   0.00868   0.0109   0.3536   0.9419
   4.250   0.4522   0.01811   0.00894   0.0111   0.2920   0.9444
   4.750   0.4989   0.01905   0.00950   0.0119   0.2199   0.9503
   5.000   0.5183   0.01944   0.00980   0.0131   0.1985   0.9540
   5.250   0.5414   0.01985   0.01015   0.0135   0.1803   0.9571
   5.500   0.5694   0.02033   0.01058   0.0130   0.1641   0.9595
   5.750   0.5956   0.02082   0.01103   0.0128   0.1511   0.9625
   6.000   0.6188   0.02135   0.01150   0.0131   0.1406   0.9660
   6.250   0.6405   0.02178   0.01200   0.0138   0.1310   0.9699
   6.500   0.6683   0.02238   0.01259   0.0133   0.1224   0.9723
   6.750   0.6952   0.02296   0.01320   0.0128   0.1144   0.9753
   7.000   0.7210   0.02361   0.01389   0.0126   0.1074   0.9792
   7.250   0.7464   0.02424   0.01457   0.0125   0.1009   0.9832
   7.500   0.7743   0.02502   0.01540   0.0118   0.0951   0.9864
   7.750   0.8008   0.02573   0.01621   0.0114   0.0892   0.9904
   8.000   0.8257   0.02659   0.01702   0.0111   0.0848   0.9946
   8.250   0.8530   0.02746   0.01811   0.0106   0.0797   0.9989
   8.500   0.8645   0.02809   0.01883   0.0129   0.0762   1.0000
   8.750   0.8701   0.02866   0.01941   0.0163   0.0738   1.0000
   9.000   0.8769   0.02944   0.02024   0.0195   0.0713   1.0000
   9.250   0.8850   0.03022   0.02122   0.0225   0.0682   1.0000
   9.500   0.8952   0.03101   0.02210   0.0249   0.0653   1.0000
   9.750   0.9077   0.03185   0.02294   0.0268   0.0629   1.0000
  10.000   0.9215   0.03302   0.02417   0.0284   0.0605   1.0000
  10.250   0.9341   0.03437   0.02583   0.0302   0.0576   1.0000
  10.500   0.9461   0.03561   0.02723   0.0318   0.0552   1.0000
  10.750   0.9579   0.03673   0.02842   0.0334   0.0533   1.0000
  11.000   0.9700   0.03790   0.02955   0.0348   0.0516   1.0000
  11.250   0.9737   0.03976   0.03174   0.0373   0.0498   1.0000
  11.500   0.9745   0.04169   0.03398   0.0398   0.0480   1.0000
  11.750   0.9752   0.04362   0.03614   0.0420   0.0467   1.0000
  12.000   0.9751   0.04562   0.03832   0.0439   0.0456   1.0000
  12.250   0.9751   0.04754   0.04037   0.0455   0.0446   1.0000
  12.500   0.9767   0.04933   0.04223   0.0468   0.0437   1.0000
  12.750   0.9778   0.05145   0.04439   0.0478   0.0430   1.0000
  13.000   0.9614   0.05510   0.04834   0.0489   0.0425   1.0000
  13.250   0.9379   0.05969   0.05326   0.0490   0.0421   1.0000
  13.500   0.9107   0.06526   0.05911   0.0477   0.0419   1.0000
  13.750   0.8796   0.07228   0.06638   0.0443   0.0420   1.0000
  14.000   0.8413   0.08202   0.07632   0.0380   0.0423   1.0000
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