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WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103.42 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxm2-il-1000000.txt
Download as CSV file: xf-fxm2-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1264   0.08726   0.08444  -0.0451   0.6491   0.0110
  -8.750  -0.1219   0.08455   0.08153  -0.0455   0.5937   0.0112
  -8.500  -0.1209   0.08074   0.07771  -0.0475   0.5861   0.0118
  -8.250  -0.1171   0.07725   0.07429  -0.0491   0.6019   0.0118
  -8.000  -0.1148   0.07442   0.07125  -0.0497   0.5406   0.0118
  -7.750  -0.1103   0.07129   0.06812  -0.0506   0.5333   0.0118
  -7.250  -0.1342   0.07581   0.07246  -0.0568   0.5268   0.0120
  -7.000  -0.1310   0.07386   0.07041  -0.0566   0.4884   0.0121
  -6.750  -0.1233   0.07175   0.06826  -0.0573   0.4791   0.0123
  -6.500  -0.1135   0.06944   0.06593  -0.0590   0.4684   0.0125
  -6.250  -0.1022   0.06688   0.06334  -0.0612   0.4569   0.0126
  -5.750  -0.0748   0.06138   0.05769  -0.0669   0.4149   0.0133
  -5.500  -0.0572   0.05830   0.05457  -0.0704   0.4091   0.0140
  -5.250  -0.0278   0.05310   0.04927  -0.0789   0.4027   0.0149
  -5.000  -0.0038   0.04926   0.04534  -0.0828   0.3973   0.0149
  -4.750   0.0213   0.04528   0.04127  -0.0863   0.3872   0.0150
  -4.500   0.0438   0.04046   0.03626  -0.0898   0.3638   0.0152
  -4.250   0.0652   0.03875   0.03445  -0.0906   0.3510   0.0154
  -4.000   0.0897   0.03689   0.03248  -0.0918   0.3442   0.0158
  -3.750   0.1276   0.03292   0.02824  -0.0946   0.3392   0.0184
  -3.500   0.1577   0.02953   0.02460  -0.0961   0.3308   0.0184
  -3.250   0.1825   0.02662   0.02150  -0.0977   0.3035   0.0189
  -3.000   0.2083   0.02561   0.02033  -0.0981   0.2923   0.0194
  -2.750   0.2419   0.02392   0.01830  -0.0980   0.2864   0.0223
  -2.500   0.2716   0.02031   0.01437  -0.0993   0.2818   0.0228
  -2.250   0.2987   0.01951   0.01351  -0.0996   0.2771   0.0232
  -2.000   0.3266   0.01871   0.01260  -0.0998   0.2685   0.0240
  -0.750   0.4741   0.01302   0.00564  -0.0995   0.2279   0.0264
  -0.500   0.5024   0.01237   0.00487  -0.0994   0.2249   0.0278
  -0.250   0.5298   0.01230   0.00480  -0.0992   0.2216   0.0293
   0.000   0.5585   0.01179   0.00423  -0.0990   0.2196   0.0297
   0.250   0.5869   0.01145   0.00384  -0.0988   0.2164   0.0303
   0.500   0.6150   0.01122   0.00357  -0.0986   0.2123   0.0310
   0.750   0.6430   0.01131   0.00358  -0.0983   0.2088   0.0321
   1.000   0.6718   0.01072   0.00304  -0.0984   0.2037   0.0335
   1.250   0.6998   0.01065   0.00287  -0.0983   0.1850   0.0346
   1.500   0.7277   0.01061   0.00277  -0.0981   0.1792   0.0356
   1.750   0.7555   0.01061   0.00273  -0.0979   0.1737   0.0367
   2.000   0.7833   0.01066   0.00275  -0.0977   0.1704   0.0380
   2.250   0.8118   0.01054   0.00262  -0.0976   0.1683   0.0398
   2.500   0.8397   0.01056   0.00263  -0.0975   0.1646   0.0415
   2.750   0.8674   0.01063   0.00267  -0.0972   0.1607   0.0433
   3.000   0.8948   0.01073   0.00274  -0.0970   0.1564   0.0452
   3.250   0.9226   0.01078   0.00279  -0.0968   0.1541   0.0498
   3.500   0.9503   0.01083   0.00287  -0.0966   0.1511   0.0640
   3.750   0.9788   0.01073   0.00304  -0.0968   0.1449   0.2662
   4.000   1.0086   0.01018   0.00334  -0.0977   0.1374   0.6991
   4.500   1.0523   0.01019   0.00372  -0.0949   0.1083   1.0000
   4.750   1.0785   0.01051   0.00395  -0.0945   0.0980   1.0000
   5.000   1.1044   0.01086   0.00420  -0.0941   0.0866   1.0000
   5.250   1.1309   0.01112   0.00442  -0.0938   0.0839   1.0000
   5.500   1.1573   0.01137   0.00463  -0.0935   0.0813   1.0000
   5.750   1.1837   0.01161   0.00484  -0.0931   0.0790   1.0000
   6.000   1.2102   0.01184   0.00505  -0.0928   0.0774   1.0000
   6.250   1.2367   0.01205   0.00527  -0.0925   0.0766   1.0000
   6.500   1.2630   0.01227   0.00548  -0.0922   0.0761   1.0000
   6.750   1.2893   0.01250   0.00571  -0.0919   0.0756   1.0000
   7.000   1.3154   0.01273   0.00594  -0.0915   0.0750   1.0000
   7.250   1.3414   0.01297   0.00619  -0.0912   0.0745   1.0000
   7.500   1.3672   0.01322   0.00645  -0.0908   0.0740   1.0000
   7.750   1.3929   0.01348   0.00671  -0.0905   0.0736   1.0000
   8.000   1.4184   0.01374   0.00699  -0.0901   0.0732   1.0000
   8.250   1.4438   0.01401   0.00729  -0.0897   0.0728   1.0000
   8.500   1.4690   0.01429   0.00758  -0.0893   0.0724   1.0000
   8.750   1.4939   0.01460   0.00790  -0.0888   0.0718   1.0000
   9.000   1.5184   0.01494   0.00826  -0.0883   0.0707   1.0000
   9.250   1.5428   0.01528   0.00862  -0.0878   0.0696   1.0000
   9.500   1.5672   0.01561   0.00897  -0.0873   0.0690   1.0000
   9.750   1.5913   0.01595   0.00934  -0.0868   0.0685   1.0000
  10.000   1.6151   0.01631   0.00975  -0.0862   0.0678   1.0000
  10.250   1.6387   0.01668   0.01016  -0.0856   0.0673   1.0000
  10.500   1.6625   0.01699   0.01051  -0.0851   0.0672   1.0000
  10.750   1.6862   0.01731   0.01087  -0.0845   0.0670   1.0000
  11.000   1.7096   0.01763   0.01124  -0.0839   0.0668   1.0000
  11.250   1.7328   0.01796   0.01163  -0.0833   0.0666   1.0000
  11.500   1.7556   0.01830   0.01202  -0.0827   0.0662   1.0000
  11.750   1.7782   0.01866   0.01244  -0.0820   0.0658   1.0000
  12.000   1.8003   0.01903   0.01287  -0.0813   0.0652   1.0000
  12.250   1.8221   0.01941   0.01331  -0.0805   0.0646   1.0000
  12.500   1.8433   0.01982   0.01378  -0.0796   0.0638   1.0000
  12.750   1.8639   0.02025   0.01427  -0.0787   0.0627   1.0000
  13.000   1.8839   0.02071   0.01478  -0.0777   0.0613   1.0000
  13.250   1.9023   0.02127   0.01536  -0.0766   0.0590   1.0000
  13.500   1.9213   0.02174   0.01587  -0.0755   0.0554   1.0000
  13.750   1.9365   0.02245   0.01654  -0.0739   0.0506   1.0000
  14.000   1.9490   0.02319   0.01728  -0.0719   0.0491   1.0000
  14.250   1.9584   0.02397   0.01810  -0.0694   0.0475   1.0000
  14.500   1.9662   0.02483   0.01901  -0.0668   0.0462   1.0000
  14.750   1.9717   0.02588   0.02014  -0.0640   0.0454   1.0000
  15.000   1.9753   0.02710   0.02144  -0.0613   0.0447   1.0000
  15.250   1.9767   0.02854   0.02297  -0.0587   0.0440   1.0000
  15.500   1.9761   0.03022   0.02473  -0.0562   0.0432   1.0000
  15.750   1.9750   0.03207   0.02668  -0.0540   0.0426   1.0000
  16.000   1.9734   0.03411   0.02882  -0.0523   0.0421   1.0000
  16.250   1.9702   0.03649   0.03131  -0.0510   0.0416   1.0000
  16.500   1.9647   0.03935   0.03429  -0.0501   0.0412   1.0000
  16.750   1.9562   0.04288   0.03795  -0.0500   0.0408   1.0000
  17.000   1.9506   0.04641   0.04162  -0.0504   0.0406   1.0000
  17.250   1.9420   0.05068   0.04604  -0.0515   0.0403   1.0000
  17.500   1.9291   0.05589   0.05141  -0.0533   0.0400   1.0000
  17.750   1.9106   0.06229   0.05798  -0.0560   0.0398   1.0000
  18.000   1.8855   0.07009   0.06596  -0.0596   0.0397   1.0000
  18.250   1.8529   0.07948   0.07554  -0.0641   0.0397   1.0000
  18.500   1.8141   0.09024   0.08649  -0.0694   0.0398   1.0000
  18.750   1.7733   0.10168   0.09812  -0.0754   0.0400   1.0000
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