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FX S 02-196 AIRFOIL (fxs02196-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX S 02-196 AIRFOIL (fxs02196-il)
Reynolds number: 50,000
Max Cl/Cd: 10.18 at α=13.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxs02196-il-50000-n5.txt
Download as CSV file: xf-fxs02196-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX S 02-196 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3799   0.08983   0.08334  -0.0853   0.9712   0.0572
 -12.000  -0.3976   0.08137   0.07470  -0.0935   0.9593   0.0569
 -11.750  -0.4146   0.07427   0.06736  -0.1005   0.9447   0.0566
 -11.500  -0.4284   0.06822   0.06100  -0.1064   0.9302   0.0565
 -11.250  -0.4371   0.06316   0.05557  -0.1111   0.9162   0.0565
 -11.000  -0.4413   0.05917   0.05121  -0.1139   0.9014   0.0566
 -10.750  -0.4455   0.05611   0.04781  -0.1146   0.8855   0.0567
 -10.500  -0.4464   0.05351   0.04485  -0.1144   0.8715   0.0570
 -10.250  -0.4405   0.05118   0.04218  -0.1139   0.8596   0.0574
 -10.000  -0.4257   0.04931   0.04010  -0.1134   0.8479   0.0581
  -9.750  -0.4056   0.04737   0.03791  -0.1132   0.8387   0.0591
  -9.500  -0.3889   0.04583   0.03611  -0.1125   0.8284   0.0606
  -9.250  -0.3694   0.04429   0.03416  -0.1118   0.8195   0.0625
  -9.000  -0.3259   0.04291   0.03272  -0.1125   0.8132   0.0652
  -8.750  -0.2816   0.04216   0.03172  -0.1123   0.8054   0.0676
  -8.500  -0.2443   0.04172   0.03123  -0.1114   0.7988   0.0700
  -8.250  -0.2181   0.04125   0.03067  -0.1101   0.7925   0.0726
  -8.000  -0.2014   0.04083   0.03021  -0.1085   0.7841   0.0750
  -7.750  -0.1878   0.04012   0.02952  -0.1070   0.7774   0.0778
  -7.500  -0.1767   0.03940   0.02874  -0.1055   0.7713   0.0812
  -7.250  -0.1727   0.03876   0.02816  -0.1036   0.7633   0.0845
  -7.000  -0.1678   0.03799   0.02735  -0.1016   0.7571   0.0893
  -6.750  -0.1636   0.03716   0.02644  -0.0997   0.7520   0.0970
  -6.500  -0.1669   0.03657   0.02586  -0.0972   0.7440   0.1051
  -6.250  -0.1692   0.03548   0.02488  -0.0952   0.7379   0.1152
  -6.000  -0.1683   0.03417   0.02371  -0.0935   0.7333   0.1407
  -5.250  -0.1622   0.03365   0.02503  -0.0841   0.7160   0.4400
  -5.000  -0.1436   0.03398   0.02506  -0.0834   0.7127   0.4887
  -4.750  -0.1308   0.03482   0.02574  -0.0813   0.7076   0.5105
  -4.500  -0.1196   0.03553   0.02632  -0.0791   0.7022   0.5254
  -4.250  -0.1022   0.03622   0.02686  -0.0774   0.6981   0.5428
  -4.000  -0.0813   0.03690   0.02737  -0.0757   0.6949   0.5612
  -3.750  -0.0570   0.03759   0.02790  -0.0740   0.6923   0.5775
  -3.500  -0.0446   0.03870   0.02900  -0.0705   0.6878   0.5888
  -3.250  -0.0425   0.03936   0.02959  -0.0678   0.6816   0.6011
  -3.000  -0.0276   0.04022   0.03041  -0.0648   0.6777   0.6131
  -2.750  -0.0099   0.04077   0.03087  -0.0626   0.6748   0.6260
  -2.500   0.0101   0.04091   0.03084  -0.0619   0.6724   0.6399
  -2.250   0.0336   0.04136   0.03121  -0.0598   0.6705   0.6481
  -2.000   0.0117   0.04265   0.03257  -0.0552   0.6627   0.6534
  -1.750   0.0214   0.04292   0.03272  -0.0546   0.6581   0.6606
  -1.500   0.0385   0.04318   0.03290  -0.0533   0.6550   0.6644
  -1.250   0.0607   0.04327   0.03286  -0.0532   0.6527   0.6682
  -1.000   0.0864   0.04328   0.03273  -0.0539   0.6510   0.6722
  -0.750   0.1149   0.04324   0.03254  -0.0552   0.6494   0.6759
  -0.500   0.0749   0.04576   0.03514  -0.0506   0.6413   0.6798
  -0.250   0.0857   0.04647   0.03581  -0.0495   0.6377   0.6828
   0.000   0.1043   0.04692   0.03619  -0.0491   0.6347   0.6864
   0.250   0.1277   0.04723   0.03642  -0.0493   0.6323   0.6907
   0.500   0.1552   0.04747   0.03655  -0.0502   0.6305   0.6949
   0.750   0.1855   0.04773   0.03668  -0.0518   0.6290   0.6991
   1.000   0.1709   0.05000   0.03898  -0.0497   0.6240   0.7023
   1.250   0.1771   0.05125   0.04024  -0.0487   0.6208   0.7055
   1.500   0.1914   0.05217   0.04113  -0.0484   0.6176   0.7090
   1.750   0.2127   0.05285   0.04175  -0.0489   0.6146   0.7125
   2.000   0.2398   0.05336   0.04219  -0.0499   0.6120   0.7160
   2.250   0.2712   0.05378   0.04252  -0.0515   0.6099   0.7198
   2.500   0.2888   0.05472   0.04344  -0.0517   0.6065   0.7232
   2.750   0.2849   0.05639   0.04515  -0.0501   0.5998   0.7263
   3.000   0.3018   0.05731   0.04606  -0.0501   0.5958   0.7301
   3.250   0.3251   0.05806   0.04679  -0.0506   0.5927   0.7343
   3.500   0.3519   0.05879   0.04749  -0.0516   0.5904   0.7390
   3.750   0.3803   0.05949   0.04817  -0.0527   0.5884   0.7437
   4.000   0.3830   0.06119   0.04993  -0.0517   0.5843   0.7480
   4.250   0.3852   0.06292   0.05171  -0.0509   0.5791   0.7530
   4.500   0.4034   0.06394   0.05275  -0.0511   0.5744   0.7590
   4.750   0.4303   0.06455   0.05338  -0.0517   0.5707   0.7653
   5.000   0.4610   0.06487   0.05374  -0.0520   0.5679   0.7718
   5.250   0.4563   0.06688   0.05582  -0.0509   0.5598   0.7781
   5.500   0.4729   0.06802   0.05700  -0.0511   0.5543   0.7853
   5.750   0.4949   0.06875   0.05781  -0.0510   0.5506   0.7927
   6.000   0.5230   0.06943   0.05855  -0.0516   0.5480   0.8019
   6.250   0.5216   0.07144   0.06067  -0.0506   0.5412   0.8101
   6.500   0.5303   0.07283   0.06216  -0.0500   0.5346   0.8207
   6.750   0.5524   0.07346   0.06289  -0.0497   0.5302   0.8337
   7.000   0.5810   0.07372   0.06327  -0.0497   0.5271   0.8508
   7.250   0.5724   0.07594   0.06564  -0.0482   0.5179   0.8691
   7.500   0.5881   0.07672   0.06658  -0.0477   0.5118   0.9026
   7.750   0.6191   0.07687   0.06682  -0.0488   0.5077   1.0000
   8.000   0.6229   0.07926   0.06924  -0.0495   0.4982   1.0000
   8.250   0.6455   0.08061   0.07063  -0.0509   0.4919   1.0000
   8.500   0.6783   0.08132   0.07135  -0.0523   0.4880   1.0000
   8.750   0.6778   0.08400   0.07409  -0.0526   0.4782   1.0000
   9.000   0.7004   0.08504   0.07518  -0.0533   0.4713   1.0000
   9.250   0.7404   0.08455   0.07472  -0.0540   0.4669   1.0000
   9.500   0.7340   0.08735   0.07758  -0.0539   0.4536   1.0000
   9.750   0.7740   0.08622   0.07648  -0.0541   0.4477   1.0000
  10.000   0.7723   0.08859   0.07893  -0.0540   0.4343   1.0000
  10.250   0.8141   0.08679   0.07718  -0.0539   0.4284   1.0000
  10.500   0.8087   0.08969   0.08016  -0.0539   0.4146   1.0000
  10.750   0.8267   0.09014   0.08069  -0.0537   0.4047   1.0000
  11.000   0.8438   0.09067   0.08130  -0.0535   0.3941   1.0000
  11.250   0.8505   0.09256   0.08328  -0.0536   0.3828   1.0000
  11.500   0.8747   0.09236   0.08317  -0.0534   0.3746   1.0000
  11.750   0.8790   0.09473   0.08566  -0.0537   0.3628   1.0000
  12.000   0.9080   0.09383   0.08487  -0.0532   0.3561   1.0000
  12.250   0.9108   0.09651   0.08765  -0.0536   0.3435   1.0000
  12.500   0.9398   0.09545   0.08672  -0.0531   0.3371   1.0000
  12.750   0.9396   0.09862   0.09000  -0.0536   0.3228   1.0000
  13.000   0.9526   0.09985   0.09136  -0.0537   0.3118   1.0000
  13.250   0.9725   0.09995   0.09159  -0.0534   0.3024   1.0000
  13.750   1.0149   0.09972   0.09159  -0.0527   0.2834   1.0000
  14.000   1.0169   0.10282   0.09481  -0.0534   0.2680   1.0000
  14.250   1.0203   0.10573   0.09785  -0.0540   0.2519   1.0000
  14.500   1.0383   0.10614   0.09833  -0.0539   0.2386   1.0000
  14.750   1.0591   0.10602   0.09822  -0.0534   0.2249   1.0000
  15.000   1.0661   0.10840   0.10070  -0.0539   0.2079   1.0000
  15.250   1.0766   0.11008   0.10237  -0.0541   0.1896   1.0000
  15.500   1.0927   0.11050   0.10252  -0.0537   0.1718   1.0000
  15.750   1.0933   0.11398   0.10602  -0.0547   0.1524   1.0000
  16.000   1.0981   0.11657   0.10845  -0.0554   0.1378   1.0000
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