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WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il)
Reynolds number: 100,000
Max Cl/Cd: 50.68 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxm2-il-100000-n5.txt
Download as CSV file: xf-fxm2-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX M2 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2686   0.09474   0.09009  -0.0155   1.0000   0.0343
  -7.000  -0.2693   0.09269   0.08812  -0.0147   1.0000   0.0348
  -6.750  -0.2723   0.09073   0.08625  -0.0138   1.0000   0.0353
  -6.500  -0.2732   0.08857   0.08418  -0.0135   1.0000   0.0358
  -6.250  -0.2720   0.08624   0.08193  -0.0140   1.0000   0.0363
  -6.000  -0.2697   0.08384   0.07960  -0.0153   1.0000   0.0370
  -5.750  -0.2647   0.08128   0.07710  -0.0184   1.0000   0.0376
  -5.500  -0.2550   0.07840   0.07424  -0.0228   1.0000   0.0379
  -5.250  -0.2274   0.07381   0.06963  -0.0300   0.9954   0.0384
  -5.000  -0.2060   0.07010   0.06598  -0.0300   0.9883   0.0400
  -4.750  -0.1461   0.06490   0.06053  -0.0471   0.9770   0.0451
  -4.500  -0.1177   0.06022   0.05588  -0.0508   0.9676   0.0460
  -4.250  -0.0932   0.05680   0.05248  -0.0528   0.9562   0.0478
  -4.000  -0.0561   0.05301   0.04859  -0.0587   0.9453   0.0511
  -3.750  -0.0073   0.04840   0.04369  -0.0676   0.9338   0.0550
  -3.500   0.0184   0.04541   0.04072  -0.0691   0.9197   0.0577
  -3.250   0.0650   0.04180   0.03677  -0.0755   0.9051   0.0655
  -3.000   0.1040   0.03892   0.03372  -0.0796   0.8870   0.0767
  -2.750   0.1439   0.03611   0.03069  -0.0834   0.8634   0.0884
  -2.250   0.2454   0.02843   0.02196  -0.0914   0.7953   0.0516
  -2.000   0.2897   0.02614   0.01908  -0.0941   0.7451   0.0514
  -1.750   0.3261   0.02439   0.01677  -0.0952   0.6943   0.0505
  -1.500   0.3588   0.02296   0.01471  -0.0955   0.6491   0.0485
  -1.250   0.3891   0.02187   0.01306  -0.0953   0.6077   0.0477
  -1.000   0.4175   0.02110   0.01192  -0.0950   0.5717   0.0492
  -0.750   0.4455   0.02053   0.01092  -0.0945   0.5414   0.0515
  -0.500   0.4734   0.01985   0.00996  -0.0940   0.5134   0.0518
  -0.250   0.5005   0.01933   0.00913  -0.0934   0.4855   0.0522
   0.000   0.5273   0.01894   0.00847  -0.0927   0.4629   0.0532
   0.250   0.5540   0.01848   0.00795  -0.0922   0.4379   0.0561
   0.500   0.5798   0.01823   0.00754  -0.0916   0.4178   0.0582
   0.750   0.6056   0.01805   0.00721  -0.0909   0.4006   0.0596
   1.000   0.6318   0.01788   0.00698  -0.0903   0.3809   0.0614
   1.250   0.6580   0.01785   0.00680  -0.0897   0.3627   0.0653
   1.500   0.6839   0.01791   0.00667  -0.0892   0.3487   0.0698
   1.750   0.7104   0.01804   0.00661  -0.0887   0.3354   0.0736
   2.000   0.7376   0.01813   0.00660  -0.0884   0.3217   0.0796
   2.250   0.7647   0.01819   0.00664  -0.0880   0.3096   0.0962
   2.500   0.7810   0.01651   0.00678  -0.0855   0.3015   1.0000
   2.750   0.8071   0.01689   0.00686  -0.0850   0.2936   1.0000
   3.000   0.8333   0.01729   0.00705  -0.0845   0.2861   1.0000
   3.250   0.8590   0.01776   0.00731  -0.0840   0.2797   1.0000
   3.500   0.8855   0.01814   0.00763  -0.0836   0.2722   1.0000
   3.750   0.9116   0.01856   0.00794  -0.0832   0.2657   1.0000
   4.000   0.9379   0.01892   0.00827  -0.0828   0.2582   1.0000
   4.250   0.9639   0.01929   0.00858  -0.0824   0.2518   1.0000
   4.500   0.9895   0.01966   0.00888  -0.0820   0.2460   1.0000
   4.750   1.0149   0.02007   0.00921  -0.0815   0.2405   1.0000
   5.000   1.0399   0.02052   0.00954  -0.0810   0.2354   1.0000
   5.250   1.0649   0.02103   0.00996  -0.0806   0.2305   1.0000
   5.500   1.0899   0.02155   0.01048  -0.0801   0.2255   1.0000
   5.750   1.1148   0.02217   0.01097  -0.0797   0.2219   1.0000
   6.000   1.1400   0.02268   0.01159  -0.0792   0.2172   1.0000
   6.250   1.1646   0.02323   0.01217  -0.0787   0.2126   1.0000
   6.500   1.1890   0.02378   0.01274  -0.0782   0.2081   1.0000
   6.750   1.2133   0.02424   0.01338  -0.0777   0.2024   1.0000
   7.000   1.2370   0.02472   0.01387  -0.0771   0.1978   1.0000
   7.250   1.2609   0.02519   0.01448  -0.0765   0.1925   1.0000
   7.500   1.2842   0.02563   0.01496  -0.0759   0.1879   1.0000
   7.750   1.3070   0.02612   0.01550  -0.0752   0.1836   1.0000
   8.000   1.3296   0.02668   0.01616  -0.0745   0.1787   1.0000
   8.250   1.3515   0.02722   0.01673  -0.0738   0.1744   1.0000
   8.500   1.3727   0.02786   0.01730  -0.0730   0.1707   1.0000
   8.750   1.3943   0.02860   0.01829  -0.0722   0.1660   1.0000
   9.000   1.4151   0.02935   0.01916  -0.0714   0.1617   1.0000
   9.250   1.4352   0.03010   0.01998  -0.0705   0.1582   1.0000
   9.500   1.4546   0.03093   0.02080  -0.0695   0.1552   1.0000
   9.750   1.4740   0.03185   0.02201  -0.0686   0.1511   1.0000
  10.000   1.4922   0.03278   0.02311  -0.0675   0.1472   1.0000
  10.250   1.5096   0.03366   0.02411  -0.0664   0.1439   1.0000
  10.500   1.5261   0.03453   0.02505  -0.0652   0.1412   1.0000
  10.750   1.5416   0.03562   0.02630  -0.0639   0.1384   1.0000
  11.000   1.5560   0.03683   0.02774  -0.0626   0.1355   1.0000
  11.250   1.5690   0.03804   0.02913  -0.0611   0.1329   1.0000
  11.500   1.5807   0.03924   0.03048  -0.0595   0.1308   1.0000
  11.750   1.5899   0.04043   0.03181  -0.0577   0.1290   1.0000
  12.000   1.5976   0.04166   0.03313  -0.0557   0.1275   1.0000
  12.250   1.6045   0.04300   0.03452  -0.0538   0.1262   1.0000
  12.500   1.6063   0.04496   0.03674  -0.0518   0.1247   1.0000
  12.750   1.6059   0.04713   0.03916  -0.0499   0.1233   1.0000
  13.000   1.6032   0.04958   0.04183  -0.0484   0.1219   1.0000
  13.250   1.5983   0.05235   0.04482  -0.0472   0.1206   1.0000
  13.500   1.5911   0.05551   0.04820  -0.0466   0.1193   1.0000
  13.750   1.5816   0.05915   0.05204  -0.0466   0.1181   1.0000
  14.000   1.5701   0.06336   0.05643  -0.0474   0.1170   1.0000
  14.250   1.5563   0.06822   0.06147  -0.0489   0.1159   1.0000
  14.500   1.5402   0.07382   0.06723  -0.0511   0.1149   1.0000
  14.750   1.5216   0.08023   0.07381  -0.0542   0.1140   1.0000
  15.000   1.5029   0.08701   0.08073  -0.0575   0.1130   1.0000
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