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FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il)
Reynolds number: 100,000
Max Cl/Cd: 5.74 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66196v-il-100000.txt
Download as CSV file: xf-fx66196v-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-196 V1 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1440   0.10743   0.10300  -0.0975   0.9143   0.1545
 -11.500  -0.1271   0.10413   0.09957  -0.1007   0.8987   0.1646
 -11.250  -0.1252   0.09967   0.09506  -0.1037   0.8846   0.1696
 -11.000  -0.1082   0.09649   0.09177  -0.1045   0.8709   0.1730
 -10.750  -0.1063   0.09269   0.08792  -0.1063   0.8592   0.1760
 -10.500  -0.3921   0.05595   0.05035  -0.1293   0.8514   0.0676
 -10.250  -0.3974   0.05401   0.04810  -0.1274   0.8398   0.0656
 -10.000  -0.3970   0.05053   0.04439  -0.1263   0.8314   0.0645
  -9.750  -0.4001   0.04787   0.04148  -0.1244   0.8209   0.0638
  -9.500  -0.3991   0.04535   0.03863  -0.1226   0.8126   0.0633
  -9.250  -0.3957   0.04318   0.03610  -0.1207   0.8042   0.0638
  -9.000  -0.3882   0.04125   0.03377  -0.1190   0.7969   0.0646
  -8.750  -0.3783   0.03967   0.03177  -0.1173   0.7894   0.0657
  -8.500  -0.3618   0.03770   0.02937  -0.1161   0.7842   0.0665
  -8.250  -0.3417   0.03518   0.02678  -0.1155   0.7769   0.0679
  -8.000  -0.3181   0.03356   0.02510  -0.1151   0.7717   0.0711
  -7.750  -0.2967   0.03252   0.02391  -0.1143   0.7661   0.0755
  -7.500  -0.2757   0.03164   0.02278  -0.1133   0.7598   0.0791
  -7.250  -0.2479   0.02992   0.02123  -0.1129   0.7555   0.0851
  -7.000  -0.2279   0.02930   0.02050  -0.1118   0.7503   0.0930
  -6.750  -0.2104   0.02841   0.01985  -0.1103   0.7447   0.1027
  -6.500  -0.1943   0.02759   0.01912  -0.1086   0.7406   0.1174
  -6.250  -0.1820   0.02661   0.01832  -0.1067   0.7373   0.1417
  -6.000  -0.1827   0.02568   0.01787  -0.1042   0.7314   0.1892
  -5.750  -0.1858   0.02472   0.01849  -0.1006   0.7271   0.4618
  -5.500  -0.1606   0.02640   0.01993  -0.0985   0.7240   0.5221
  -5.250  -0.1347   0.02828   0.02180  -0.0956   0.7211   0.5473
  -5.000  -0.1212   0.02998   0.02351  -0.0925   0.7159   0.5655
  -4.750  -0.1019   0.03132   0.02476  -0.0899   0.7123   0.5848
  -4.500  -0.0783   0.03260   0.02595  -0.0871   0.7095   0.6024
  -4.250  -0.0514   0.03387   0.02714  -0.0841   0.7074   0.6190
  -4.000  -0.0425   0.03528   0.02857  -0.0803   0.7030   0.6322
  -3.750  -0.0363   0.03680   0.03013  -0.0758   0.6986   0.6418
  -3.500  -0.0255   0.03749   0.03075  -0.0733   0.6956   0.6540
  -3.250  -0.0101   0.03773   0.03085  -0.0722   0.6934   0.6666
  -3.000   0.0134   0.03818   0.03123  -0.0701   0.6918   0.6738
  -2.750  -0.0145   0.03988   0.03296  -0.0666   0.6879   0.6822
  -2.500  -0.1023   0.04368   0.03703  -0.0557   0.6840   0.6835
  -2.250  -0.2597   0.05234   0.04618  -0.0512   0.8000   0.6631
  -2.000  -0.2699   0.05198   0.04584  -0.0454   0.7922   0.6730
  -1.750  -0.2544   0.05298   0.04679  -0.0427   0.7888   0.6892
  -1.500  -0.2298   0.05404   0.04772  -0.0424   0.7865   0.7016
  -1.250  -0.1984   0.05545   0.04898  -0.0437   0.7850   0.7091
  -1.000  -0.2032   0.05456   0.04797  -0.0413   0.7769   0.7140
  -0.750  -0.1789   0.05520   0.04852  -0.0413   0.7727   0.7181
  -0.500  -0.1451   0.05646   0.04964  -0.0432   0.7702   0.7233
  -0.250  -0.1422   0.05638   0.04946  -0.0417   0.7645   0.7274
   0.000  -0.1188   0.05684   0.04978  -0.0428   0.7589   0.7307
   0.250  -0.0908   0.05778   0.05063  -0.0438   0.7559   0.7337
   0.500  -0.0549   0.05937   0.05211  -0.0462   0.7540   0.7368
   0.750  -0.0599   0.05880   0.05150  -0.0434   0.7447   0.7396
   1.000  -0.0295   0.05981   0.05237  -0.0453   0.7408   0.7433
   1.250   0.0052   0.06133   0.05378  -0.0478   0.7387   0.7469
   1.500   0.0019   0.06123   0.05367  -0.0450   0.7309   0.7496
   1.750   0.0282   0.06212   0.05450  -0.0460   0.7259   0.7528
   2.000   0.0629   0.06368   0.05597  -0.0482   0.7233   0.7563
   2.250   0.0638   0.06394   0.05619  -0.0466   0.7160   0.7598
   2.500   0.0893   0.06487   0.05706  -0.0476   0.7104   0.7634
   2.750   0.1226   0.06646   0.05861  -0.0493   0.7077   0.7669
   3.000   0.1593   0.06875   0.06086  -0.0517   0.7063   0.7710
   3.250   0.1454   0.06783   0.05994  -0.0483   0.6951   0.7745
   3.500   0.1788   0.06947   0.06153  -0.0502   0.6921   0.7790
   3.750   0.2165   0.07190   0.06395  -0.0524   0.6906   0.7838
   4.000   0.2006   0.07110   0.06318  -0.0489   0.6795   0.7882
   4.250   0.2325   0.07280   0.06485  -0.0506   0.6766   0.7946
   4.500   0.2693   0.07523   0.06730  -0.0527   0.6750   0.8008
   4.750   0.2568   0.07470   0.06680  -0.0498   0.6635   0.8062
   5.000   0.2890   0.07654   0.06864  -0.0514   0.6608   0.8132
   5.250   0.3244   0.07917   0.07129  -0.0536   0.6591   0.8220
   5.500   0.3125   0.07864   0.07081  -0.0508   0.6473   0.8286
   5.750   0.3482   0.08075   0.07296  -0.0527   0.6447   0.8400
   6.000   0.3400   0.08122   0.07350  -0.0506   0.6348   0.8491
   6.250   0.3692   0.08277   0.07514  -0.0518   0.6305   0.8644
   6.500   0.4065   0.08516   0.07764  -0.0538   0.6285   0.8869
   6.750   0.3968   0.08532   0.07796  -0.0521   0.6171   0.9133
   7.000   0.4381   0.08745   0.08019  -0.0560   0.6136   1.0000
   7.250   0.4365   0.08886   0.08160  -0.0563   0.6042   1.0000
   7.500   0.4722   0.09100   0.08369  -0.0594   0.5994   1.0000
   7.750   0.5175   0.09422   0.08689  -0.0630   0.5972   1.0000
   8.000   0.5037   0.09471   0.08738  -0.0614   0.5851   1.0000
   8.250   0.5449   0.09745   0.09011  -0.0640   0.5822   1.0000
   8.500   0.5336   0.09852   0.09120  -0.0627   0.5706   1.0000
   8.750   0.5737   0.10093   0.09363  -0.0648   0.5669   1.0000
   9.000   0.5630   0.10241   0.09514  -0.0637   0.5558   1.0000
   9.250   0.6009   0.10460   0.09735  -0.0654   0.5516   1.0000
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