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WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il)
Reynolds number: 200,000
Max Cl/Cd: 65.06 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxm2-il-200000.txt
Download as CSV file: xf-fxm2-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2851   0.10385   0.10039  -0.0172   1.0000   0.0267
  -8.000  -0.2921   0.10275   0.09937  -0.0185   1.0000   0.0268
  -7.750  -0.2963   0.10102   0.09770  -0.0183   1.0000   0.0268
  -7.500  -0.2797   0.09571   0.09241  -0.0161   1.0000   0.0272
  -7.250  -0.2756   0.09298   0.08973  -0.0148   1.0000   0.0274
  -7.000  -0.2757   0.09081   0.08761  -0.0135   1.0000   0.0277
  -6.750  -0.2789   0.08886   0.08574  -0.0118   1.0000   0.0280
  -6.500  -0.2813   0.08686   0.08380  -0.0108   1.0000   0.0283
  -6.250  -0.2810   0.08463   0.08163  -0.0105   1.0000   0.0286
  -6.000  -0.2802   0.08234   0.07940  -0.0105   1.0000   0.0290
  -5.750  -0.2784   0.07996   0.07707  -0.0110   1.0000   0.0294
  -5.500  -0.2750   0.07748   0.07465  -0.0119   1.0000   0.0299
  -5.250  -0.2695   0.07487   0.07207  -0.0134   1.0000   0.0305
  -5.000  -0.1963   0.06810   0.06509  -0.0369   0.9931   0.0320
  -4.750  -0.1653   0.06285   0.05984  -0.0418   0.9870   0.0324
  -4.500  -0.1327   0.05885   0.05587  -0.0456   0.9816   0.0332
  -4.250  -0.0942   0.05473   0.05170  -0.0519   0.9729   0.0348
  -4.000  -0.0161   0.04834   0.04482  -0.0688   0.9668   0.0383
  -3.750   0.0043   0.04495   0.04159  -0.0694   0.9563   0.0394
  -3.500   0.0501   0.04140   0.03793  -0.0755   0.9501   0.0431
  -3.250   0.0961   0.03716   0.03335  -0.0812   0.9377   0.0463
  -3.000   0.1313   0.03433   0.03052  -0.0842   0.9262   0.0488
  -2.750   0.1837   0.03086   0.02663  -0.0898   0.9142   0.0554
  -2.500   0.2214   0.02846   0.02419  -0.0927   0.8943   0.0602
  -2.250   0.2657   0.02606   0.02154  -0.0964   0.8643   0.0704
  -2.000   0.3195   0.02587   0.02053  -0.1002   0.8082   0.0868
  -1.750   0.3484   0.02235   0.01688  -0.1016   0.7398   0.0926
  -1.500   0.3745   0.02141   0.01549  -0.1012   0.6783   0.1067
   0.000   0.5422   0.01641   0.00784  -0.0965   0.4604   0.0785
   0.250   0.5697   0.01622   0.00734  -0.0957   0.4308   0.0746
   0.500   0.5958   0.01563   0.00655  -0.0950   0.4098   0.0720
   0.750   0.6226   0.01530   0.00609  -0.0943   0.3882   0.0708
   1.000   0.6494   0.01507   0.00576  -0.0938   0.3678   0.0719
   1.250   0.6757   0.01506   0.00556  -0.0932   0.3530   0.0745
   1.500   0.7021   0.01508   0.00545  -0.0927   0.3402   0.0754
   1.750   0.7296   0.01493   0.00531  -0.0925   0.3276   0.0780
   2.000   0.7573   0.01491   0.00526  -0.0923   0.3156   0.0836
   2.250   0.7848   0.01493   0.00520  -0.0920   0.3055   0.0916
   2.500   0.8120   0.01503   0.00525  -0.0917   0.2968   0.1123
   2.750   0.8272   0.01359   0.00547  -0.0889   0.2900   1.0000
   3.000   0.8535   0.01402   0.00568  -0.0885   0.2807   1.0000
   3.250   0.8801   0.01435   0.00591  -0.0881   0.2714   1.0000
   3.500   0.9067   0.01463   0.00610  -0.0877   0.2635   1.0000
   3.750   0.9333   0.01486   0.00625  -0.0873   0.2564   1.0000
   4.000   0.9601   0.01508   0.00643  -0.0870   0.2501   1.0000
   4.250   0.9864   0.01537   0.00662  -0.0866   0.2454   1.0000
   4.500   1.0127   0.01573   0.00691  -0.0862   0.2409   1.0000
   4.750   1.0387   0.01611   0.00721  -0.0859   0.2365   1.0000
   5.000   1.0645   0.01663   0.00759  -0.0855   0.2323   1.0000
   5.250   1.0905   0.01704   0.00801  -0.0851   0.2276   1.0000
   5.500   1.1162   0.01758   0.00847  -0.0848   0.2232   1.0000
   5.750   1.1418   0.01804   0.00895  -0.0844   0.2188   1.0000
   6.000   1.1674   0.01842   0.00936  -0.0840   0.2141   1.0000
   6.250   1.1929   0.01893   0.00980  -0.0836   0.2103   1.0000
   6.500   1.2181   0.01918   0.01021  -0.0831   0.2058   1.0000
   6.750   1.2433   0.01946   0.01055  -0.0826   0.2012   1.0000
   7.000   1.2681   0.01977   0.01086  -0.0821   0.1972   1.0000
   7.250   1.2930   0.02001   0.01122  -0.0816   0.1922   1.0000
   7.500   1.3175   0.02025   0.01148  -0.0810   0.1877   1.0000
   7.750   1.3415   0.02064   0.01189  -0.0804   0.1832   1.0000
   8.000   1.3653   0.02102   0.01235  -0.0798   0.1780   1.0000
   8.250   1.3883   0.02152   0.01280  -0.0792   0.1732   1.0000
   8.500   1.4111   0.02215   0.01351  -0.0785   0.1683   1.0000
   8.750   1.4338   0.02268   0.01415  -0.0777   0.1630   1.0000
   9.000   1.4557   0.02329   0.01477  -0.0770   0.1583   1.0000
   9.250   1.4771   0.02411   0.01560  -0.0762   0.1541   1.0000
   9.500   1.4990   0.02468   0.01634  -0.0753   0.1498   1.0000
   9.750   1.5203   0.02528   0.01703  -0.0745   0.1459   1.0000
  10.000   1.5410   0.02594   0.01771  -0.0736   0.1429   1.0000
  10.250   1.5612   0.02689   0.01863  -0.0727   0.1401   1.0000
  10.500   1.5813   0.02762   0.01956  -0.0718   0.1377   1.0000
  10.750   1.6009   0.02842   0.02051  -0.0708   0.1353   1.0000
  11.000   1.6200   0.02923   0.02143  -0.0697   0.1332   1.0000
  11.250   1.6386   0.03004   0.02235  -0.0686   0.1313   1.0000
  11.500   1.6565   0.03087   0.02326  -0.0675   0.1297   1.0000
  11.750   1.6738   0.03174   0.02417  -0.0664   0.1279   1.0000
  12.000   1.6911   0.03295   0.02540  -0.0653   0.1260   1.0000
  12.250   1.7049   0.03403   0.02671  -0.0638   0.1248   1.0000
  12.500   1.7172   0.03513   0.02801  -0.0621   0.1232   1.0000
  12.750   1.7267   0.03620   0.02926  -0.0600   0.1214   1.0000
  13.000   1.7347   0.03727   0.03047  -0.0578   0.1197   1.0000
  13.250   1.7420   0.03836   0.03167  -0.0556   0.1181   1.0000
  13.500   1.7487   0.03950   0.03292  -0.0536   0.1165   1.0000
  13.750   1.7554   0.04081   0.03429  -0.0518   0.1149   1.0000
  14.000   1.7656   0.04244   0.03594  -0.0506   0.1131   1.0000
  14.250   1.7667   0.04448   0.03817  -0.0488   0.1119   1.0000
  14.500   1.7622   0.04675   0.04069  -0.0470   0.1109   1.0000
  14.750   1.7564   0.04937   0.04356  -0.0456   0.1098   1.0000
  15.000   1.7493   0.05235   0.04677  -0.0448   0.1087   1.0000
  15.250   1.7407   0.05573   0.05036  -0.0446   0.1075   1.0000
  15.500   1.7311   0.05952   0.05436  -0.0449   0.1063   1.0000
  15.750   1.7207   0.06367   0.05870  -0.0458   0.1052   1.0000
  16.000   1.7103   0.06808   0.06327  -0.0471   0.1040   1.0000
  16.250   1.7008   0.07260   0.06793  -0.0487   0.1028   1.0000
  16.500   1.6941   0.07690   0.07232  -0.0503   0.1016   1.0000
  16.750   1.6895   0.08106   0.07655  -0.0516   0.1001   1.0000
  17.000   1.6612   0.08931   0.08499  -0.0555   0.0989   1.0000
  17.250   1.5869   0.10658   0.10264  -0.0665   0.0987   1.0000
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