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FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 63-120 AIRFOIL (fx63120-il)
Reynolds number: 100,000
Max Cl/Cd: 64.71 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63120-il-100000.txt
Download as CSV file: xf-fx63120-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-120 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2956   0.11667   0.11175  -0.0401   1.0000   0.0966
  -9.500  -0.3205   0.11671   0.11194  -0.0407   1.0000   0.0985
  -9.250  -0.3464   0.11680   0.11219  -0.0399   1.0000   0.0990
  -9.000  -0.3415   0.11240   0.10784  -0.0374   1.0000   0.1002
  -8.750  -0.3232   0.10907   0.10450  -0.0336   1.0000   0.1029
  -8.500  -0.3274   0.10766   0.10314  -0.0309   1.0000   0.1053
  -8.250  -0.3374   0.10655   0.10211  -0.0286   1.0000   0.1084
  -8.000  -0.2946   0.10068   0.09674  -0.0304   0.9925   0.1164
  -7.750  -0.2693   0.09700   0.09303  -0.0314   0.9881   0.1229
  -7.500  -0.2830   0.09388   0.08996  -0.0376   0.9817   0.1289
  -7.250  -0.2723   0.08886   0.08495  -0.0395   0.9765   0.1318
  -7.000  -0.3797   0.09843   0.09434  -0.0229   0.9962   0.1218
  -6.500  -0.3628   0.09099   0.08695  -0.0342   0.9812   0.1333
  -6.250  -0.3503   0.08398   0.07992  -0.0569   0.9683   0.1461
  -6.000  -0.3325   0.08287   0.07882  -0.0461   0.9657   0.1486
  -5.750  -0.3119   0.07681   0.07272  -0.0607   0.9565   0.1630
  -5.500  -0.2947   0.07625   0.07218  -0.0525   0.9523   0.1676
  -5.250  -0.2658   0.07037   0.06619  -0.0697   0.9433   0.1934
  -5.000  -0.2522   0.06870   0.06459  -0.0638   0.9380   0.1985
  -4.750  -0.1121   0.03772   0.03106  -0.1218   0.9389   0.0956
  -4.500  -0.0591   0.03427   0.02702  -0.1283   0.9361   0.0943
  -4.250  -0.0053   0.03152   0.02370  -0.1339   0.9338   0.0927
  -4.000   0.0278   0.03024   0.02207  -0.1355   0.9269   0.0952
  -3.750   0.0722   0.02897   0.02044  -0.1386   0.9224   0.0980
  -3.500   0.1192   0.02743   0.01876  -0.1420   0.9194   0.1010
  -3.250   0.1464   0.02676   0.01816  -0.1424   0.9113   0.1066
  -3.000   0.1895   0.02593   0.01728  -0.1449   0.9065   0.1150
  -2.750   0.2349   0.02499   0.01647  -0.1481   0.9025   0.1289
  -2.500   0.2707   0.02419   0.01594  -0.1502   0.8946   0.1650
  -2.250   0.3240   0.02312   0.01615  -0.1551   0.8909   0.5037
  -2.000   0.3543   0.02356   0.01662  -0.1548   0.8840   0.5499
  -1.750   0.3797   0.02407   0.01718  -0.1533   0.8759   0.5910
  -1.500   0.4153   0.02424   0.01742  -0.1529   0.8720   0.6283
  -1.250   0.4285   0.02482   0.01802  -0.1499   0.8610   0.6509
  -1.000   0.4695   0.02460   0.01774  -0.1512   0.8570   0.6737
  -0.750   0.4953   0.02480   0.01789  -0.1510   0.8481   0.6881
  -0.500   0.5336   0.02453   0.01758  -0.1523   0.8427   0.7024
  -0.250   0.5799   0.02402   0.01701  -0.1549   0.8395   0.7183
   0.000   0.5981   0.02434   0.01735  -0.1533   0.8284   0.7306
   0.250   0.6415   0.02382   0.01679  -0.1555   0.8243   0.7459
   0.500   0.6648   0.02400   0.01698  -0.1547   0.8144   0.7606
   0.750   0.7033   0.02355   0.01652  -0.1560   0.8089   0.7786
   1.000   0.7300   0.02355   0.01654  -0.1556   0.8001   0.7971
   1.250   0.7621   0.02319   0.01619  -0.1557   0.7931   0.8177
   1.500   0.7847   0.02311   0.01615  -0.1542   0.7843   0.8400
   1.750   0.8112   0.02274   0.01581  -0.1531   0.7766   0.8655
   2.000   0.8278   0.02268   0.01581  -0.1506   0.7667   0.8944
   2.250   0.8507   0.02206   0.01524  -0.1486   0.7595   0.9361
   2.500   0.8860   0.02208   0.01527  -0.1504   0.7486   1.0000
   2.750   0.9377   0.02161   0.01474  -0.1545   0.7422   1.0000
   3.000   0.9726   0.02181   0.01493  -0.1562   0.7301   1.0000
   3.250   1.0131   0.02160   0.01467  -0.1582   0.7201   1.0000
   3.500   1.0537   0.02124   0.01426  -0.1599   0.7099   1.0000
   3.750   1.0842   0.02135   0.01437  -0.1603   0.6968   1.0000
   4.000   1.1162   0.02139   0.01440  -0.1608   0.6848   1.0000
   4.250   1.1536   0.02115   0.01411  -0.1619   0.6750   1.0000
   4.500   1.1826   0.02126   0.01424  -0.1619   0.6619   1.0000
   4.750   1.2100   0.02145   0.01445  -0.1616   0.6486   1.0000
   5.000   1.2385   0.02156   0.01460  -0.1614   0.6354   1.0000
   5.250   1.2680   0.02163   0.01467  -0.1613   0.6225   1.0000
   5.500   1.2978   0.02164   0.01467  -0.1612   0.6091   1.0000
   5.750   1.3261   0.02168   0.01471  -0.1608   0.5942   1.0000
   6.000   1.3505   0.02174   0.01479  -0.1597   0.5761   1.0000
   6.250   1.3741   0.02177   0.01483  -0.1585   0.5563   1.0000
   6.500   1.3983   0.02184   0.01489  -0.1574   0.5365   1.0000
   6.750   1.4227   0.02202   0.01503  -0.1564   0.5176   1.0000
   7.000   1.4449   0.02233   0.01534  -0.1551   0.4978   1.0000
   7.250   1.4649   0.02274   0.01579  -0.1535   0.4760   1.0000
   7.500   1.4856   0.02317   0.01616  -0.1520   0.4541   1.0000
   7.750   1.5025   0.02374   0.01673  -0.1500   0.4296   1.0000
   8.000   1.5188   0.02436   0.01722  -0.1479   0.4043   1.0000
   8.250   1.5302   0.02509   0.01800  -0.1451   0.3769   1.0000
   8.500   1.5403   0.02592   0.01878  -0.1423   0.3496   1.0000
   8.750   1.5481   0.02687   0.01965  -0.1391   0.3227   1.0000
   9.000   1.5521   0.02799   0.02068  -0.1355   0.2958   1.0000
   9.250   1.5529   0.02931   0.02191  -0.1315   0.2694   1.0000
   9.500   1.5521   0.03092   0.02336  -0.1276   0.2446   1.0000
   9.750   1.5508   0.03276   0.02508  -0.1240   0.2209   1.0000
  10.000   1.5505   0.03480   0.02696  -0.1208   0.2000   1.0000
  10.250   1.5516   0.03688   0.02898  -0.1179   0.1812   1.0000
  10.500   1.5541   0.03900   0.03105  -0.1154   0.1655   1.0000
  10.750   1.5579   0.04116   0.03316  -0.1132   0.1520   1.0000
  11.000   1.5637   0.04334   0.03527  -0.1113   0.1404   1.0000
  11.250   1.5735   0.04548   0.03727  -0.1098   0.1300   1.0000
  11.500   1.5795   0.04766   0.03963  -0.1081   0.1212   1.0000
  11.750   1.5915   0.04986   0.04181  -0.1068   0.1133   1.0000
  12.000   1.6024   0.05196   0.04394  -0.1056   0.1065   1.0000
  12.250   1.6156   0.05432   0.04638  -0.1045   0.1001   1.0000
  12.500   1.6246   0.05660   0.04879  -0.1033   0.0947   1.0000
  12.750   1.6434   0.05904   0.05121  -0.1026   0.0891   1.0000
  13.000   1.6445   0.06187   0.05435  -0.1011   0.0853   1.0000
  13.250   1.6567   0.06422   0.05670  -0.1003   0.0808   1.0000
  13.500   1.6670   0.06754   0.06019  -0.0994   0.0771   1.0000
  13.750   1.6605   0.07111   0.06412  -0.0980   0.0747   1.0000
  14.000   1.6570   0.07458   0.06782  -0.0969   0.0720   1.0000
  14.250   1.6840   0.07754   0.07061  -0.0969   0.0673   1.0000
  14.500   1.6647   0.08194   0.07542  -0.0958   0.0666   1.0000
  14.750   1.6459   0.08693   0.08079  -0.0953   0.0658   1.0000
  15.000   1.6261   0.09236   0.08660  -0.0954   0.0650   1.0000
  15.250   1.6046   0.09831   0.09289  -0.0963   0.0643   1.0000
  15.500   1.5817   0.10477   0.09967  -0.0979   0.0638   1.0000
  15.750   1.5568   0.11189   0.10711  -0.1005   0.0635   1.0000
  16.000   1.5279   0.12027   0.11580  -0.1045   0.0637   1.0000
  16.250   1.4956   0.12992   0.12575  -0.1100   0.0642   1.0000
  16.500   1.4606   0.14110   0.13717  -0.1171   0.0651   1.0000
  16.750   1.4238   0.15401   0.15028  -0.1260   0.0661   1.0000
  17.000   1.3880   0.16824   0.16464  -0.1361   0.0671   1.0000
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