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FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 61-140 AIRFOIL (fx61140-il)
Reynolds number: 100,000
Max Cl/Cd: 51.64 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61140-il-100000.txt
Download as CSV file: xf-fx61140-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-140 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4426   0.09888   0.09437  -0.0461   1.0000   0.1215
  -9.250  -0.3961   0.09691   0.09229  -0.0382   1.0000   0.1274
  -9.000  -0.4179   0.09287   0.08839  -0.0418   1.0000   0.1345
  -8.750  -0.4120   0.08937   0.08494  -0.0404   1.0000   0.1395
  -8.500  -0.4165   0.08630   0.08195  -0.0405   1.0000   0.1468
  -8.250  -0.4724   0.08126   0.07710  -0.0451   1.0000   0.1491
  -8.000  -0.4343   0.07951   0.07535  -0.0403   1.0000   0.1596
  -6.000  -0.5269   0.04092   0.03449  -0.0455   1.0000   0.0642
  -5.750  -0.5039   0.03693   0.02967  -0.0455   1.0000   0.0541
  -5.500  -0.4607   0.03429   0.02655  -0.0490   0.9950   0.0536
  -5.250  -0.4169   0.03059   0.02251  -0.0527   0.9884   0.0549
  -5.000  -0.3717   0.02818   0.01981  -0.0554   0.9809   0.0548
  -4.750  -0.3274   0.02606   0.01765  -0.0581   0.9736   0.0572
  -4.500  -0.2849   0.02469   0.01618  -0.0605   0.9632   0.0646
  -4.250  -0.2455   0.02295   0.01463  -0.0626   0.9532   0.0740
  -4.000  -0.1989   0.02117   0.01301  -0.0666   0.9442   0.1010
  -3.750  -0.1639   0.01959   0.01421  -0.0667   0.9345   0.6280
  -3.500  -0.1403   0.02177   0.01627  -0.0612   0.9201   0.6701
  -3.250  -0.1265   0.02405   0.01851  -0.0524   0.9064   0.7025
  -3.000  -0.1095   0.02562   0.01999  -0.0448   0.8939   0.7325
  -2.750  -0.0754   0.02579   0.01996  -0.0439   0.8831   0.7534
  -2.500  -0.0249   0.02540   0.01930  -0.0472   0.8766   0.7667
  -2.250   0.0120   0.02502   0.01873  -0.0476   0.8645   0.7752
  -2.000   0.0515   0.02453   0.01805  -0.0495   0.8521   0.7851
  -1.750   0.0907   0.02406   0.01738  -0.0520   0.8391   0.7953
  -1.500   0.1298   0.02362   0.01676  -0.0534   0.8262   0.8022
  -1.250   0.1636   0.02324   0.01620  -0.0550   0.8121   0.8106
  -1.000   0.1973   0.02290   0.01572  -0.0559   0.7984   0.8174
  -0.750   0.2257   0.02263   0.01529  -0.0565   0.7847   0.8249
  -0.500   0.2559   0.02237   0.01489  -0.0569   0.7717   0.8311
  -0.250   0.2825   0.02218   0.01456  -0.0573   0.7593   0.8381
   0.000   0.3101   0.02195   0.01422  -0.0572   0.7472   0.8437
   0.250   0.3309   0.02187   0.01406  -0.0567   0.7346   0.8506
   0.500   0.3548   0.02168   0.01381  -0.0560   0.7231   0.8559
   0.750   0.3787   0.02160   0.01365  -0.0558   0.7124   0.8619
   1.000   0.4068   0.02147   0.01340  -0.0562   0.7030   0.8673
   1.250   0.4273   0.02139   0.01332  -0.0552   0.6920   0.8726
   1.500   0.4489   0.02142   0.01331  -0.0548   0.6821   0.8783
   1.750   0.4786   0.02129   0.01309  -0.0552   0.6739   0.8828
   2.000   0.4975   0.02131   0.01315  -0.0541   0.6637   0.8879
   2.250   0.5208   0.02140   0.01321  -0.0540   0.6549   0.8932
   2.500   0.5473   0.02132   0.01311  -0.0539   0.6467   0.8975
   2.750   0.5675   0.02143   0.01328  -0.0531   0.6376   0.9026
   3.250   0.6157   0.02157   0.01343  -0.0526   0.6210   0.9119
   3.500   0.6421   0.02167   0.01353  -0.0528   0.6135   0.9168
   3.750   0.6648   0.02183   0.01376  -0.0524   0.6049   0.9215
   4.000   0.6885   0.02197   0.01395  -0.0521   0.5971   0.9261
   4.250   0.7144   0.02210   0.01411  -0.0522   0.5893   0.9310
   4.500   0.7357   0.02237   0.01448  -0.0517   0.5811   0.9358
   4.750   0.7650   0.02247   0.01462  -0.0522   0.5739   0.9403
   5.000   0.7844   0.02284   0.01513  -0.0515   0.5655   0.9458
   5.250   0.8161   0.02296   0.01526  -0.0524   0.5588   0.9503
   5.500   0.8356   0.02340   0.01588  -0.0518   0.5500   0.9558
   5.750   0.8698   0.02353   0.01603  -0.0531   0.5435   0.9606
   6.000   0.8911   0.02404   0.01677  -0.0529   0.5340   0.9666
   6.250   0.9216   0.02436   0.01719  -0.0539   0.5263   0.9721
   6.500   0.9543   0.02472   0.01769  -0.0555   0.5174   0.9777
   6.750   0.9834   0.02529   0.01849  -0.0566   0.5083   0.9848
   7.000   1.0264   0.02542   0.01867  -0.0596   0.5004   0.9911
   7.250   1.0441   0.02607   0.01956  -0.0589   0.4900   1.0000
   7.500   1.0696   0.02646   0.02009  -0.0591   0.4800   1.0000
   7.750   1.1030   0.02641   0.02011  -0.0602   0.4693   1.0000
   8.000   1.1363   0.02618   0.01997  -0.0611   0.4565   1.0000
   8.250   1.1641   0.02599   0.01991  -0.0613   0.4413   1.0000
   8.500   1.1882   0.02559   0.01966  -0.0609   0.4222   1.0000
   8.750   1.2160   0.02495   0.01907  -0.0608   0.4022   1.0000
   9.000   1.2410   0.02474   0.01898  -0.0606   0.3835   1.0000
   9.250   1.2602   0.02468   0.01920  -0.0597   0.3610   1.0000
   9.500   1.2765   0.02472   0.01942  -0.0583   0.3336   1.0000
   9.750   1.2860   0.02512   0.01991  -0.0562   0.2939   1.0000
  10.000   1.2779   0.02660   0.02111  -0.0522   0.2238   1.0000
  10.250   1.2569   0.02988   0.02379  -0.0483   0.1564   1.0000
  10.500   1.2375   0.03374   0.02729  -0.0458   0.1232   1.0000
  10.750   1.2239   0.03765   0.03106  -0.0446   0.1028   1.0000
  11.000   1.2144   0.04156   0.03490  -0.0444   0.0878   1.0000
  11.250   1.2074   0.04551   0.03882  -0.0448   0.0749   1.0000
  11.500   1.2018   0.04948   0.04279  -0.0453   0.0645   1.0000
  11.750   1.1979   0.05332   0.04657  -0.0453   0.0561   1.0000
  12.000   1.1981   0.05682   0.05002  -0.0454   0.0481   1.0000
  12.250   1.2053   0.05978   0.05307  -0.0450   0.0416   1.0000
  12.500   1.2266   0.06184   0.05491  -0.0429   0.0360   1.0000
  12.750   1.2425   0.06459   0.05795  -0.0425   0.0340   1.0000
  13.000   1.2585   0.06772   0.06134  -0.0420   0.0325   1.0000
  13.250   1.2680   0.07149   0.06543  -0.0420   0.0316   1.0000
  13.500   1.2703   0.07585   0.07010  -0.0424   0.0311   1.0000
  13.750   1.2664   0.08074   0.07529  -0.0434   0.0309   1.0000
  14.000   1.2570   0.08619   0.08106  -0.0450   0.0309   1.0000
  14.250   1.2437   0.09213   0.08731  -0.0473   0.0311   1.0000
  14.500   1.2277   0.09854   0.09401  -0.0503   0.0313   1.0000
  14.750   1.2090   0.10561   0.10136  -0.0540   0.0315   1.0000
  15.000   1.1898   0.11313   0.10914  -0.0585   0.0320   1.0000
  15.250   1.1688   0.12140   0.11765  -0.0638   0.0324   1.0000
  15.500   1.1472   0.13039   0.12685  -0.0700   0.0329   1.0000
  15.750   1.1258   0.14000   0.13664  -0.0769   0.0334   1.0000
  16.000   1.1046   0.15040   0.14714  -0.0845   0.0341   1.0000
  16.250   1.0828   0.16196   0.15879  -0.0927   0.0349   1.0000
  16.500   1.0697   0.17198   0.16883  -0.0993   0.0356   1.0000
  16.750   1.0245   0.20026   0.19704  -0.1165   0.0440   1.0000
  17.000   1.0320   0.20526   0.20203  -0.1189   0.0458   1.0000
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