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WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il)
Reynolds number: 500,000
Max Cl/Cd: 94.41 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxm2-il-500000.txt
Download as CSV file: xf-fxm2-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2920   0.10522   0.10297  -0.0144   1.0000   0.0149
  -8.500  -0.2931   0.10284   0.10062  -0.0157   1.0000   0.0149
  -8.250  -0.2937   0.10046   0.09828  -0.0163   1.0000   0.0150
  -8.000  -0.2883   0.09691   0.09476  -0.0151   1.0000   0.0151
  -7.750  -0.2866   0.09455   0.09244  -0.0145   1.0000   0.0151
  -7.500  -0.2821   0.09208   0.08999  -0.0130   1.0000   0.0153
  -7.250  -0.2802   0.08994   0.08790  -0.0124   0.9998   0.0155
  -7.000  -0.2585   0.08627   0.08422  -0.0174   0.9965   0.0159
  -6.750  -0.2395   0.08272   0.08069  -0.0220   0.9920   0.0165
  -6.500  -0.2184   0.07885   0.07683  -0.0273   0.9859   0.0172
  -6.250  -0.1886   0.07428   0.07225  -0.0366   0.9806   0.0182
  -6.000  -0.1548   0.06876   0.06669  -0.0509   0.9698   0.0184
  -5.750  -0.0830   0.05020   0.04826  -0.0520   0.9373   0.0189
  -5.500  -0.0483   0.04520   0.04320  -0.0601   0.9167   0.0193
  -5.250  -0.0760   0.05673   0.05460  -0.0639   0.9346   0.0190
  -5.000  -0.0185   0.05163   0.04938  -0.0761   0.9066   0.0197
  -4.750   0.0271   0.04723   0.04463  -0.0850   0.8361   0.0209
  -4.500   0.0678   0.04213   0.03896  -0.0924   0.7692   0.0223
  -4.250   0.0848   0.03863   0.03513  -0.0933   0.7109   0.0226
  -4.000   0.1011   0.03702   0.03328  -0.0929   0.6609   0.0229
  -3.750   0.1223   0.03526   0.03129  -0.0934   0.6151   0.0236
  -3.500   0.1480   0.03311   0.02889  -0.0945   0.5872   0.0248
  -3.250   0.1862   0.02901   0.02418  -0.0967   0.5544   0.0272
  -3.000   0.2088   0.02734   0.02238  -0.0971   0.5314   0.0276
  -2.750   0.2346   0.02585   0.02072  -0.0976   0.4999   0.0285
  -2.500   0.2626   0.02431   0.01885  -0.0979   0.4755   0.0305
  -2.250   0.2961   0.02182   0.01582  -0.0984   0.4562   0.0327
  -2.000   0.3217   0.02070   0.01453  -0.0986   0.4210   0.0335
  -1.750   0.3492   0.01983   0.01346  -0.0986   0.4052   0.0359
  -1.500   0.3806   0.01840   0.01160  -0.0987   0.3913   0.0390
  -1.250   0.4078   0.01744   0.01052  -0.0988   0.3650   0.0405
  -1.000   0.4365   0.01800   0.01069  -0.0980   0.3495   0.0451
  -0.750   0.4643   0.01598   0.00857  -0.0986   0.3388   0.0479
  -0.500   0.4931   0.01562   0.00798  -0.0984   0.3223   0.0554
  -0.250   0.5199   0.01510   0.00738  -0.0984   0.2988   0.0607
   0.000   0.5474   0.01513   0.00715  -0.0982   0.2878   0.0766
   0.250   0.5742   0.01450   0.00647  -0.0982   0.2796   0.0894
   0.500   0.6058   0.01345   0.00508  -0.0968   0.2736   0.0455
   0.750   0.6338   0.01292   0.00450  -0.0965   0.2658   0.0456
   1.000   0.6619   0.01265   0.00421  -0.0962   0.2541   0.0453
   1.250   0.6897   0.01228   0.00377  -0.0961   0.2442   0.0456
   1.500   0.7176   0.01205   0.00348  -0.0960   0.2384   0.0467
   1.750   0.7450   0.01203   0.00341  -0.0958   0.2323   0.0494
   2.000   0.7725   0.01207   0.00341  -0.0955   0.2268   0.0509
   2.250   0.7992   0.01224   0.00350  -0.0952   0.2216   0.0526
   2.500   0.8275   0.01220   0.00348  -0.0950   0.2175   0.0548
   2.750   0.8551   0.01225   0.00353  -0.0948   0.2132   0.0611
   3.000   0.8826   0.01234   0.00363  -0.0946   0.2091   0.0741
   3.250   0.9140   0.01123   0.00390  -0.0959   0.2035   0.7105
   3.750   0.9581   0.01092   0.00400  -0.0927   0.1929   1.0000
   4.000   0.9854   0.01108   0.00408  -0.0924   0.1876   1.0000
   4.250   1.0124   0.01127   0.00421  -0.0922   0.1833   1.0000
   4.500   1.0393   0.01147   0.00436  -0.0919   0.1797   1.0000
   4.750   1.0660   0.01170   0.00454  -0.0916   0.1761   1.0000
   5.000   1.0924   0.01197   0.00475  -0.0912   0.1723   1.0000
   5.250   1.1190   0.01218   0.00496  -0.0909   0.1698   1.0000
   5.500   1.1458   0.01236   0.00516  -0.0906   0.1669   1.0000
   5.750   1.1723   0.01259   0.00538  -0.0903   0.1636   1.0000
   6.000   1.1984   0.01284   0.00562  -0.0899   0.1599   1.0000
   6.250   1.2240   0.01316   0.00591  -0.0895   0.1559   1.0000
   6.500   1.2505   0.01334   0.00613  -0.0892   0.1533   1.0000
   6.750   1.2769   0.01354   0.00634  -0.0889   0.1492   1.0000
   7.000   1.3028   0.01380   0.00658  -0.0885   0.1436   1.0000
   7.250   1.3284   0.01408   0.00686  -0.0881   0.1381   1.0000
   7.500   1.3539   0.01436   0.00712  -0.0877   0.1301   1.0000
   7.750   1.3787   0.01471   0.00741  -0.0873   0.1223   1.0000
   8.000   1.4031   0.01511   0.00777  -0.0868   0.1157   1.0000
   8.250   1.4275   0.01549   0.00815  -0.0863   0.1109   1.0000
   8.500   1.4519   0.01586   0.00853  -0.0857   0.1074   1.0000
   8.750   1.4758   0.01628   0.00895  -0.0852   0.1040   1.0000
   9.000   1.4993   0.01673   0.00940  -0.0846   0.1010   1.0000
   9.250   1.5227   0.01715   0.00987  -0.0839   0.0987   1.0000
   9.500   1.5465   0.01752   0.01029  -0.0833   0.0975   1.0000
   9.750   1.5699   0.01791   0.01074  -0.0827   0.0963   1.0000
  10.000   1.5929   0.01833   0.01121  -0.0820   0.0947   1.0000
  10.250   1.6153   0.01878   0.01170  -0.0813   0.0927   1.0000
  10.500   1.6372   0.01927   0.01223  -0.0805   0.0908   1.0000
  10.750   1.6583   0.01982   0.01280  -0.0797   0.0888   1.0000
  11.000   1.6788   0.02039   0.01342  -0.0787   0.0871   1.0000
  11.250   1.6998   0.02088   0.01399  -0.0778   0.0864   1.0000
  11.500   1.7201   0.02140   0.01459  -0.0769   0.0857   1.0000
  11.750   1.7398   0.02195   0.01522  -0.0758   0.0849   1.0000
  12.000   1.7586   0.02253   0.01588  -0.0747   0.0840   1.0000
  12.250   1.7765   0.02315   0.01658  -0.0734   0.0832   1.0000
  12.500   1.7932   0.02381   0.01731  -0.0720   0.0823   1.0000
  12.750   1.8080   0.02452   0.01810  -0.0704   0.0814   1.0000
  13.000   1.8197   0.02528   0.01894  -0.0682   0.0805   1.0000
  13.250   1.8292   0.02613   0.01986  -0.0658   0.0797   1.0000
  13.500   1.8368   0.02710   0.02090  -0.0633   0.0787   1.0000
  13.750   1.8427   0.02821   0.02210  -0.0608   0.0778   1.0000
  14.000   1.8469   0.02949   0.02347  -0.0583   0.0770   1.0000
  14.250   1.8550   0.03059   0.02470  -0.0565   0.0766   1.0000
  14.500   1.8617   0.03185   0.02609  -0.0547   0.0761   1.0000
  14.750   1.8672   0.03328   0.02765  -0.0531   0.0755   1.0000
  15.000   1.8713   0.03491   0.02941  -0.0517   0.0747   1.0000
  15.250   1.8740   0.03678   0.03141  -0.0505   0.0738   1.0000
  15.500   1.8746   0.03898   0.03374  -0.0496   0.0728   1.0000
  15.750   1.8728   0.04162   0.03650  -0.0490   0.0718   1.0000
  16.000   1.8681   0.04483   0.03982  -0.0491   0.0708   1.0000
  16.250   1.8601   0.04874   0.04385  -0.0497   0.0698   1.0000
  16.500   1.8490   0.05337   0.04859  -0.0509   0.0689   1.0000
  16.750   1.8351   0.05866   0.05401  -0.0527   0.0680   1.0000
  17.000   1.8227   0.06396   0.05945  -0.0547   0.0672   1.0000
  17.250   1.8161   0.06868   0.06435  -0.0567   0.0667   1.0000
  17.500   1.8059   0.07404   0.06987  -0.0591   0.0661   1.0000
  17.750   1.7929   0.08000   0.07601  -0.0619   0.0653   1.0000
  18.000   1.7773   0.08647   0.08264  -0.0649   0.0646   1.0000
  18.250   1.7606   0.09330   0.08963  -0.0683   0.0638   1.0000
  18.500   1.7433   0.10042   0.09689  -0.0720   0.0629   1.0000
  18.750   1.7258   0.10769   0.10430  -0.0758   0.0619   1.0000
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