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WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=100,000 Ncrit=0


Details Polar file
Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il)
Reynolds number: 100,000
Max Cl/Cd: 56.41 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx62k131-il-100000.txt
Download as CSV file: xf-fx62k131-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 62-K-131 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3349   0.13907   0.13433  -0.0461   1.0001   0.0612
 -11.250  -0.3490   0.13848   0.13383  -0.0439   1.0001   0.0623
 -11.000  -0.3649   0.13800   0.13344  -0.0423   1.0001   0.0630
 -10.750  -0.3806   0.13735   0.13288  -0.0413   1.0001   0.0635
 -10.500  -0.3960   0.13643   0.13204  -0.0408   1.0001   0.0638
 -10.250  -0.4104   0.13520   0.13089  -0.0405   1.0001   0.0640
 -10.000  -0.4034   0.13004   0.12577  -0.0379   1.0001   0.0652
  -9.750  -0.3920   0.12692   0.12263  -0.0344   1.0001   0.0678
  -9.500  -0.3954   0.12484   0.12059  -0.0329   1.0001   0.0698
  -9.250  -0.4014   0.12275   0.11855  -0.0319   1.0001   0.0718
  -9.000  -0.4097   0.12066   0.11651  -0.0313   1.0001   0.0739
  -8.750  -0.4224   0.11868   0.11460  -0.0313   1.0001   0.0757
  -8.500  -0.4403   0.11692   0.11292  -0.0319   1.0001   0.0767
  -8.250  -0.4601   0.11510   0.11119  -0.0325   1.0001   0.0772
  -8.000  -0.4805   0.11315   0.10932  -0.0326   1.0001   0.0774
  -7.750  -0.4667   0.10801   0.10420  -0.0308   0.9992   0.0796
  -7.500  -0.4470   0.10473   0.10088  -0.0305   0.9968   0.0842
  -7.250  -0.4488   0.10131   0.09750  -0.0334   0.9932   0.0875
  -7.000  -0.4634   0.09811   0.09435  -0.0367   0.9887   0.0896
  -6.750  -0.4791   0.09207   0.08826  -0.0495   0.9833   0.0910
  -6.500  -0.4849   0.08637   0.08243  -0.0559   0.9788   0.0926
  -6.250  -0.4600   0.08440   0.08066  -0.0495   0.9766   0.0981
  -6.000  -0.4646   0.07879   0.07440  -0.0657   0.9706   0.1059
  -5.750  -0.4497   0.07460   0.07065  -0.0600   0.9681   0.1097
  -5.500  -0.4332   0.06949   0.06525  -0.0676   0.9638   0.1217
  -5.250  -0.4106   0.06544   0.06105  -0.0720   0.9600   0.1359
  -5.000  -0.3943   0.06207   0.05761  -0.0738   0.9556   0.1504
  -4.750  -0.3712   0.05894   0.05449  -0.0755   0.9518   0.1680
  -4.500  -0.3368   0.05556   0.05096  -0.0808   0.9483   0.2082
  -4.000  -0.1942   0.04109   0.03381  -0.0992   0.9419   0.0743
  -3.750  -0.1435   0.03802   0.02996  -0.1026   0.9387   0.0621
  -3.500  -0.0944   0.03528   0.02682  -0.1062   0.9361   0.0578
  -3.250  -0.0585   0.03374   0.02500  -0.1073   0.9323   0.0571
  -3.000  -0.0292   0.03273   0.02387  -0.1075   0.9276   0.0595
  -2.750   0.0100   0.03165   0.02276  -0.1097   0.9241   0.0676
  -2.500   0.0620   0.03058   0.02175  -0.1143   0.9215   0.0815
  -2.250   0.0998   0.02884   0.02288  -0.1153   0.9185   0.7049
  -2.000   0.0900   0.03028   0.02430  -0.1055   0.9111   0.7539
  -1.750   0.0843   0.03142   0.02538  -0.0964   0.9048   0.7909
  -1.500   0.0679   0.03208   0.02607  -0.0855   0.8973   0.8243
  -1.250   0.0512   0.03238   0.02637  -0.0743   0.8907   0.8617
  -1.000   0.0361   0.03222   0.02620  -0.0645   0.8834   0.8959
  -0.750   0.0326   0.03183   0.02572  -0.0573   0.8771   0.9261
  -0.500   0.0446   0.03161   0.02532  -0.0549   0.8698   0.9405
  -0.250   0.0812   0.03165   0.02511  -0.0568   0.8654   0.9514
   0.000   0.0928   0.03160   0.02495  -0.0552   0.8566   0.9623
   0.250   0.1341   0.03168   0.02482  -0.0582   0.8520   0.9716
   0.500   0.1564   0.03185   0.02487  -0.0588   0.8433   0.9817
   0.750   0.2056   0.03208   0.02493  -0.0635   0.8385   0.9895
   1.000   0.2276   0.03233   0.02512  -0.0642   0.8289   0.9998
   1.250   0.2708   0.03264   0.02528  -0.0677   0.8242   0.9999
   1.500   0.2887   0.03318   0.02577  -0.0679   0.8145   0.9999
   1.750   0.3347   0.03346   0.02596  -0.0717   0.8101   0.9999
   2.000   0.3551   0.03408   0.02655  -0.0722   0.8001   0.9999
   2.250   0.4029   0.03428   0.02668  -0.0761   0.7960   0.9999
   2.500   0.4240   0.03496   0.02736  -0.0768   0.7856   0.9999
   2.750   0.4728   0.03503   0.02740  -0.0806   0.7818   0.9999
   3.000   0.4941   0.03574   0.02813  -0.0812   0.7710   0.9999
   3.250   0.5434   0.03566   0.02805  -0.0848   0.7675   0.9999
   3.500   0.5645   0.03642   0.02884  -0.0854   0.7564   0.9999
   3.750   0.5916   0.03706   0.02952  -0.0867   0.7470   0.9999
   4.000   0.6345   0.03699   0.02953  -0.0893   0.7419   0.9999
   4.250   0.6595   0.03771   0.03030  -0.0903   0.7316   0.9999
   4.500   0.7058   0.03736   0.03004  -0.0931   0.7275   0.9999
   4.750   0.7298   0.03808   0.03087  -0.0938   0.7165   0.9999
   5.000   0.7783   0.03740   0.03030  -0.0966   0.7131   0.9999
   5.250   0.8015   0.03808   0.03110  -0.0971   0.7016   0.9999
   5.500   0.8526   0.03703   0.03023  -0.0998   0.6989   0.9999
   5.750   0.8762   0.03762   0.03096  -0.1002   0.6870   0.9999
   6.000   0.9281   0.03616   0.02968  -0.1025   0.6845   0.9999
   6.500   1.0109   0.03388   0.02784  -0.1048   0.6706   0.9999
   6.750   1.0486   0.03242   0.02660  -0.1050   0.6592   0.9999
   7.000   1.0944   0.03007   0.02448  -0.1056   0.6481   0.9999
   7.250   1.1461   0.02751   0.02222  -0.1069   0.6370   0.9999
   7.500   1.1937   0.02538   0.02034  -0.1080   0.6214   0.9999
   7.750   1.2333   0.02362   0.01876  -0.1079   0.5959   0.9999
   8.000   1.2633   0.02256   0.01774  -0.1068   0.5576   0.9999
   8.250   1.2799   0.02269   0.01784  -0.1046   0.5116   0.9999
   8.500   1.2897   0.02341   0.01845  -0.1019   0.4587   0.9999
   8.750   1.2913   0.02478   0.01964  -0.0984   0.3926   0.9999
   9.000   1.2810   0.02716   0.02149  -0.0941   0.3085   0.9999
   9.250   1.2635   0.03051   0.02416  -0.0899   0.2157   0.9999
   9.500   1.2453   0.03438   0.02732  -0.0862   0.1453   0.9999
   9.750   1.2328   0.03806   0.03052  -0.0832   0.1029   0.9999
  10.000   1.2273   0.04132   0.03353  -0.0811   0.0703   0.9999
  10.250   1.2208   0.04472   0.03682  -0.0786   0.0540   0.9999
  10.500   1.2208   0.04772   0.03982  -0.0763   0.0441   0.9999
  10.750   1.2304   0.05027   0.04237  -0.0741   0.0379   0.9999
  11.000   1.2433   0.05245   0.04459  -0.0731   0.0328   0.9999
  11.250   1.2734   0.05485   0.04703  -0.0719   0.0292   0.9999
  11.500   1.3047   0.05758   0.05009  -0.0711   0.0279   0.9999
  11.750   1.3263   0.06118   0.05409  -0.0702   0.0274   0.9999
  12.000   1.3349   0.06522   0.05855  -0.0688   0.0273   0.9999
  12.250   1.3348   0.06946   0.06319  -0.0673   0.0275   0.9999
  12.500   1.3282   0.07396   0.06806  -0.0658   0.0277   0.9999
  12.750   1.3177   0.07862   0.07306  -0.0645   0.0280   0.9999
  13.000   1.3045   0.08346   0.07821  -0.0636   0.0283   0.9999
  13.250   1.2890   0.08853   0.08357  -0.0631   0.0286   0.9999
  13.500   1.2723   0.09382   0.08913  -0.0633   0.0289   0.9999
  13.750   1.2540   0.09954   0.09510  -0.0640   0.0292   0.9999
  14.000   1.2358   0.10546   0.10123  -0.0654   0.0295   0.9999
  14.250   1.2176   0.11191   0.10788  -0.0675   0.0298   0.9999
  14.750   0.9663   0.10201   0.09834  -0.0419   0.0298   0.9999
  15.000   0.9436   0.10774   0.10425  -0.0447   0.0300   0.9999
  15.250   0.9231   0.11357   0.11021  -0.0476   0.0304   0.9999
  15.500   0.9022   0.11946   0.11632  -0.0516   0.0307   0.9999
  15.750   0.8682   0.12847   0.12558  -0.0584   0.0317   0.9999
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