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WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.47 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxm2-il-1000000-n5.txt
Download as CSV file: xf-fxm2-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1965   0.09699   0.09275  -0.0475   0.3351   0.0059
  -9.000  -0.1959   0.09245   0.08822  -0.0491   0.3280   0.0066
  -8.750  -0.1892   0.08983   0.08555  -0.0500   0.3023   0.0065
  -8.500  -0.1829   0.08731   0.08299  -0.0509   0.2912   0.0067
  -8.250  -0.1757   0.08448   0.08029  -0.0520   0.3269   0.0067
  -8.000  -0.1681   0.08262   0.07829  -0.0525   0.2861   0.0068
  -7.750  -0.1669   0.07907   0.07477  -0.0536   0.2861   0.0067
  -7.500  -0.1578   0.07740   0.07311  -0.0540   0.2847   0.0069
  -7.250  -0.1538   0.07516   0.07089  -0.0543   0.2831   0.0069
  -7.000  -0.1529   0.07242   0.06816  -0.0553   0.2798   0.0069
  -6.750  -0.1436   0.06979   0.06554  -0.0574   0.2791   0.0070
  -6.500  -0.1315   0.06732   0.06308  -0.0598   0.2778   0.0072
  -6.250  -0.1185   0.06430   0.06006  -0.0629   0.2765   0.0073
  -6.000  -0.1036   0.06093   0.05668  -0.0667   0.2751   0.0075
  -5.750  -0.0862   0.05742   0.05315  -0.0707   0.2718   0.0077
  -5.500  -0.0663   0.05310   0.04878  -0.0756   0.2695   0.0077
  -5.000  -0.0129   0.03876   0.03411  -0.0900   0.2654   0.0092
  -4.750   0.0130   0.03676   0.03198  -0.0916   0.2439   0.0094
  -4.500   0.0402   0.03424   0.02929  -0.0934   0.2392   0.0097
  -3.500   0.1655   0.01407   0.00717  -0.1015   0.2299   0.0152
  -3.250   0.1933   0.01410   0.00715  -0.1013   0.2272   0.0154
  -3.000   0.2210   0.01416   0.00717  -0.1010   0.2245   0.0156
  -2.750   0.2490   0.01391   0.00684  -0.1009   0.2220   0.0160
  -2.500   0.2775   0.01321   0.00601  -0.1008   0.2207   0.0166
  -2.250   0.3062   0.01196   0.00453  -0.1009   0.2191   0.0179
  -2.000   0.3345   0.01148   0.00394  -0.1007   0.2163   0.0184
  -1.750   0.3626   0.01128   0.00368  -0.1006   0.2116   0.0190
  -1.500   0.3907   0.01127   0.00366  -0.1003   0.2075   0.0194
  -1.250   0.4184   0.01129   0.00357  -0.1001   0.1852   0.0200
  -1.000   0.4464   0.01116   0.00336  -0.0999   0.1789   0.0208
  -0.750   0.4744   0.01099   0.00311  -0.0997   0.1730   0.0215
  -0.500   0.5025   0.01086   0.00292  -0.0995   0.1695   0.0221
  -0.250   0.5308   0.01071   0.00273  -0.0994   0.1665   0.0227
   0.000   0.5587   0.01070   0.00270  -0.0992   0.1622   0.0234
   0.250   0.5865   0.01074   0.00271  -0.0989   0.1574   0.0242
   0.500   0.6145   0.01072   0.00266  -0.0987   0.1541   0.0251
   0.750   0.6426   0.01068   0.00260  -0.0986   0.1507   0.0260
   1.000   0.6704   0.01071   0.00257  -0.0983   0.1440   0.0266
   1.250   0.6969   0.01094   0.00260  -0.0980   0.1130   0.0274
   1.500   0.7240   0.01109   0.00268  -0.0977   0.0987   0.0284
   1.750   0.7510   0.01127   0.00280  -0.0974   0.0836   0.0297
   2.000   0.7783   0.01140   0.00287  -0.0971   0.0769   0.0307
   2.250   0.8059   0.01147   0.00293  -0.0969   0.0760   0.0316
   2.500   0.8334   0.01156   0.00299  -0.0967   0.0746   0.0326
   2.750   0.8609   0.01164   0.00307  -0.0964   0.0734   0.0342
   3.000   0.8883   0.01175   0.00317  -0.0962   0.0724   0.0362
   3.250   0.9156   0.01187   0.00327  -0.0959   0.0716   0.0377
   3.500   0.9429   0.01199   0.00338  -0.0957   0.0707   0.0399
   3.750   0.9701   0.01212   0.00351  -0.0954   0.0698   0.0436
   4.000   0.9974   0.01222   0.00367  -0.0952   0.0690   0.0854
   4.250   1.0253   0.01221   0.00388  -0.0952   0.0683   0.2483
   4.500   1.0526   0.01230   0.00405  -0.0951   0.0676   0.3049
   4.750   1.0800   0.01237   0.00423  -0.0950   0.0672   0.3716
   5.000   1.1080   0.01231   0.00445  -0.0951   0.0669   0.5137
   5.250   1.1363   0.01215   0.00471  -0.0954   0.0666   0.7062
   5.500   1.1547   0.01175   0.00488  -0.0932   0.0662   1.0000
   5.750   1.1814   0.01195   0.00506  -0.0929   0.0656   1.0000
   6.000   1.2080   0.01215   0.00526  -0.0926   0.0650   1.0000
   6.250   1.2345   0.01236   0.00547  -0.0923   0.0642   1.0000
   6.500   1.2608   0.01258   0.00568  -0.0920   0.0632   1.0000
   6.750   1.2870   0.01281   0.00590  -0.0916   0.0617   1.0000
   7.000   1.3128   0.01309   0.00615  -0.0913   0.0596   1.0000
   7.250   1.3387   0.01334   0.00640  -0.0909   0.0579   1.0000
   7.500   1.3639   0.01366   0.00670  -0.0905   0.0499   1.0000
   7.750   1.3886   0.01406   0.00704  -0.0900   0.0461   1.0000
   8.000   1.4138   0.01436   0.00733  -0.0896   0.0457   1.0000
   8.250   1.4389   0.01466   0.00764  -0.0892   0.0454   1.0000
   8.500   1.4638   0.01497   0.00796  -0.0887   0.0450   1.0000
   8.750   1.4884   0.01531   0.00830  -0.0882   0.0444   1.0000
   9.000   1.5125   0.01570   0.00870  -0.0877   0.0433   1.0000
   9.250   1.5366   0.01607   0.00909  -0.0872   0.0424   1.0000
   9.500   1.5606   0.01642   0.00946  -0.0866   0.0419   1.0000
   9.750   1.5845   0.01677   0.00984  -0.0861   0.0417   1.0000
  10.000   1.6082   0.01714   0.01023  -0.0855   0.0415   1.0000
  10.250   1.6316   0.01751   0.01064  -0.0849   0.0413   1.0000
  10.500   1.6546   0.01790   0.01106  -0.0843   0.0411   1.0000
  10.750   1.6774   0.01830   0.01150  -0.0836   0.0409   1.0000
  11.000   1.6998   0.01872   0.01196  -0.0829   0.0408   1.0000
  11.250   1.7219   0.01914   0.01243  -0.0821   0.0407   1.0000
  11.500   1.7436   0.01958   0.01291  -0.0814   0.0406   1.0000
  11.750   1.7648   0.02004   0.01343  -0.0805   0.0405   1.0000
  12.000   1.7855   0.02052   0.01396  -0.0796   0.0404   1.0000
  12.250   1.8056   0.02101   0.01451  -0.0786   0.0403   1.0000
  12.500   1.8251   0.02153   0.01508  -0.0776   0.0402   1.0000
  12.750   1.8439   0.02207   0.01569  -0.0765   0.0401   1.0000
  13.000   1.8618   0.02263   0.01632  -0.0752   0.0400   1.0000
  13.250   1.8786   0.02323   0.01699  -0.0738   0.0397   1.0000
  13.500   1.8928   0.02388   0.01772  -0.0720   0.0392   1.0000
  13.750   1.9033   0.02460   0.01852  -0.0697   0.0387   1.0000
  14.000   1.9120   0.02540   0.01940  -0.0671   0.0382   1.0000
  14.250   1.9202   0.02628   0.02035  -0.0647   0.0379   1.0000
  14.500   1.9268   0.02730   0.02145  -0.0623   0.0375   1.0000
  14.750   1.9310   0.02852   0.02277  -0.0598   0.0369   1.0000
  15.000   1.9332   0.02998   0.02431  -0.0574   0.0363   1.0000
  15.250   1.9339   0.03164   0.02608  -0.0553   0.0358   1.0000
  15.500   1.9325   0.03362   0.02816  -0.0534   0.0352   1.0000
  15.750   1.9395   0.03502   0.02964  -0.0522   0.0349   1.0000
  16.000   1.9446   0.03668   0.03140  -0.0513   0.0345   1.0000
  16.250   1.9468   0.03875   0.03357  -0.0505   0.0341   1.0000
  16.500   1.9471   0.04121   0.03615  -0.0502   0.0337   1.0000
  16.750   1.9454   0.04410   0.03915  -0.0502   0.0332   1.0000
  17.000   1.9411   0.04757   0.04274  -0.0508   0.0324   1.0000
  17.250   1.9340   0.05172   0.04702  -0.0519   0.0314   1.0000
  17.500   1.9224   0.05679   0.05222  -0.0538   0.0298   1.0000
  17.750   1.9043   0.06317   0.05876  -0.0564   0.0287   1.0000
  18.000   1.8795   0.07095   0.06671  -0.0600   0.0284   1.0000
  18.250   1.8466   0.08044   0.07639  -0.0646   0.0285   1.0000
  18.500   1.8058   0.09162   0.08779  -0.0703   0.0295   1.0000
  18.750   1.7606   0.10401   0.10039  -0.0768   0.0305   1.0000
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