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GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il)
Reynolds number: 200,000
Max Cl/Cd: 73.34 at α=0.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe244-il-200000.txt
Download as CSV file: xf-goe244-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 244 (MVA PR.4) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.2901   0.10440   0.10045  -0.1364   0.8906   0.0565
  -9.750   0.3002   0.10189   0.09791  -0.1373   0.8862   0.0581
  -9.500   0.2893   0.10091   0.09694  -0.1406   0.8780   0.0599
  -9.250   0.3001   0.09780   0.09383  -0.1407   0.8721   0.0604
  -9.000   0.3205   0.09471   0.09071  -0.1396   0.8682   0.0611
  -8.750   0.3329   0.09265   0.08864  -0.1393   0.8622   0.0622
  -8.500   0.3421   0.09067   0.08666  -0.1395   0.8550   0.0638
  -8.250   0.3454   0.08854   0.08450  -0.1418   0.8498   0.0664
  -8.000   0.3383   0.08652   0.08251  -0.1449   0.8415   0.0673
  -7.750   0.3581   0.08388   0.07985  -0.1433   0.8363   0.0679
  -7.500   0.3758   0.08147   0.07740  -0.1430   0.8319   0.0689
  -7.250   0.3875   0.07953   0.07545  -0.1431   0.8258   0.0702
  -7.000   0.3954   0.07764   0.07357  -0.1435   0.8181   0.0721
  -6.750   0.3797   0.07517   0.07107  -0.1506   0.8113   0.0751
  -6.500   0.3950   0.07310   0.06903  -0.1475   0.8042   0.0757
  -6.250   0.4129   0.07113   0.06705  -0.1465   0.7987   0.0766
  -6.000   0.4289   0.06920   0.06507  -0.1466   0.7944   0.0781
  -5.750   0.4379   0.06756   0.06344  -0.1472   0.7883   0.0801
  -5.500   0.4403   0.06380   0.05971  -0.1570   0.7800   0.0844
  -5.250   0.4599   0.06199   0.05785  -0.1551   0.7759   0.0853
  -5.000   0.4761   0.06056   0.05641  -0.1543   0.7704   0.0868
  -4.750   0.4885   0.05897   0.05485  -0.1550   0.7630   0.0898
  -4.500   0.5148   0.05451   0.05033  -0.1653   0.7576   0.0956
  -4.250   0.5339   0.05316   0.04895  -0.1647   0.7523   0.0974
  -4.000   0.7133   0.02616   0.02019  -0.2387   0.7460   0.0657
  -3.750   0.7586   0.02386   0.01752  -0.2433   0.7406   0.0631
  -3.500   0.8067   0.02196   0.01504  -0.2477   0.7360   0.0612
  -3.250   0.8330   0.02137   0.01443  -0.2477   0.7276   0.0621
  -3.000   0.8675   0.02059   0.01349  -0.2489   0.7209   0.0634
  -2.750   0.9006   0.01988   0.01261  -0.2499   0.7140   0.0640
  -2.500   0.9299   0.01929   0.01195  -0.2500   0.7054   0.0644
  -2.250   0.9650   0.01864   0.01114  -0.2510   0.6988   0.0653
  -2.000   0.9906   0.01835   0.01085  -0.2505   0.6891   0.0664
  -1.750   1.0236   0.01783   0.01029  -0.2513   0.6811   0.0682
  -1.500   1.0502   0.01760   0.01013  -0.2511   0.6706   0.0707
  -1.250   1.0830   0.01732   0.00971  -0.2517   0.6615   0.0748
  -1.000   1.1096   0.01713   0.00958  -0.2517   0.6490   0.0815
  -0.750   1.1409   0.01684   0.00920  -0.2524   0.6368   0.0953
  -0.500   1.1760   0.01630   0.00899  -0.2542   0.6233   0.2715
  -0.250   1.1986   0.01646   0.00914  -0.2531   0.6074   0.3042
   0.000   1.2207   0.01668   0.00928  -0.2519   0.5905   0.3264
   0.250   1.2417   0.01693   0.00945  -0.2506   0.5728   0.3453
   0.500   1.2618   0.01725   0.00965  -0.2491   0.5545   0.3625
   0.750   1.2810   0.01762   0.00991  -0.2474   0.5368   0.3773
   1.000   1.2996   0.01805   0.01024  -0.2457   0.5206   0.3929
   1.250   1.3179   0.01854   0.01061  -0.2439   0.5065   0.4109
   1.500   1.3365   0.01906   0.01099  -0.2422   0.4943   0.4284
   1.750   1.3551   0.01953   0.01139  -0.2406   0.4834   0.4452
   2.250   1.3930   0.02050   0.01223  -0.2375   0.4664   0.4751
   2.500   1.4137   0.02101   0.01263  -0.2363   0.4591   0.4927
   2.750   1.4357   0.02151   0.01307  -0.2353   0.4526   0.5105
   3.000   1.4562   0.02198   0.01353  -0.2341   0.4464   0.5274
   3.250   1.4800   0.02246   0.01391  -0.2335   0.4410   0.5436
   3.500   1.5071   0.02292   0.01429  -0.2335   0.4362   0.5571
   3.750   1.5272   0.02337   0.01479  -0.2324   0.4318   0.5696
   4.000   1.5494   0.02384   0.01523  -0.2316   0.4275   0.5830
   4.250   1.5731   0.02427   0.01566  -0.2310   0.4236   0.5944
   4.500   1.6033   0.02472   0.01599  -0.2316   0.4199   0.6071
   4.750   1.6292   0.02523   0.01648  -0.2315   0.4166   0.6198
   5.000   1.6486   0.02570   0.01704  -0.2303   0.4135   0.6296
   5.250   1.6705   0.02620   0.01756  -0.2296   0.4103   0.6406
   5.500   1.6935   0.02667   0.01805  -0.2291   0.4073   0.6510
   5.750   1.7183   0.02713   0.01849  -0.2288   0.4043   0.6622
   6.000   1.7495   0.02761   0.01888  -0.2297   0.4013   0.6757
   6.250   1.7776   0.02816   0.01944  -0.2300   0.3983   0.6886
   6.500   1.7903   0.02875   0.02015  -0.2279   0.3955   0.7004
   6.750   1.8058   0.02933   0.02081  -0.2262   0.3924   0.7142
   7.000   1.8229   0.02986   0.02140  -0.2248   0.3890   0.7297
   7.250   1.8432   0.03032   0.02186  -0.2239   0.3858   0.7465
   7.500   1.8704   0.03074   0.02224  -0.2241   0.3827   0.7664
   7.750   1.8993   0.03125   0.02277  -0.2247   0.3797   0.7966
   8.000   1.9050   0.03177   0.02355  -0.2215   0.3776   1.0000
   8.250   1.9180   0.03258   0.02443  -0.2198   0.3752   1.0000
   8.500   1.9323   0.03336   0.02525  -0.2183   0.3726   1.0000
   8.750   1.9477   0.03407   0.02596  -0.2169   0.3696   1.0000
   9.000   1.9671   0.03465   0.02651  -0.2160   0.3666   1.0000
   9.250   1.9940   0.03515   0.02692  -0.2163   0.3639   1.0000
   9.500   2.0251   0.03581   0.02752  -0.2172   0.3615   1.0000
   9.750   2.0262   0.03692   0.02880  -0.2138   0.3595   1.0000
  10.000   2.0284   0.03807   0.03010  -0.2108   0.3570   1.0000
  10.250   2.0332   0.03917   0.03129  -0.2081   0.3540   1.0000
  10.500   2.0432   0.04008   0.03226  -0.2062   0.3511   1.0000
  10.750   2.0594   0.04078   0.03296  -0.2050   0.3485   1.0000
  11.000   2.0829   0.04124   0.03337  -0.2048   0.3459   1.0000
  11.250   2.1104   0.04182   0.03391  -0.2052   0.3431   1.0000
  11.500   2.1012   0.04361   0.03591  -0.2011   0.3410   1.0000
  11.750   2.0965   0.04536   0.03784  -0.1978   0.3384   1.0000
  12.000   2.0965   0.04695   0.03956  -0.1951   0.3357   1.0000
  12.250   2.1025   0.04822   0.04091  -0.1931   0.3329   1.0000
  12.500   2.1164   0.04898   0.04167  -0.1920   0.3299   1.0000
  12.750   2.1442   0.04901   0.04159  -0.1922   0.3266   1.0000
  13.000   2.1345   0.05129   0.04406  -0.1889   0.3236   1.0000
  13.250   2.1155   0.05426   0.04726  -0.1850   0.3203   1.0000
  13.500   2.1080   0.05655   0.04968  -0.1823   0.3165   1.0000
  13.750   2.1158   0.05764   0.05077  -0.1809   0.3125   1.0000
  14.000   2.1446   0.05721   0.05017  -0.1810   0.3081   1.0000
  14.250   2.1121   0.06189   0.05518  -0.1772   0.3047   1.0000
  14.500   2.0946   0.06564   0.05913  -0.1748   0.3003   1.0000
  14.750   2.0957   0.06766   0.06119  -0.1735   0.2959   1.0000
  15.000   2.1191   0.06742   0.06080  -0.1731   0.2915   1.0000
  15.250   2.0830   0.07365   0.06736  -0.1706   0.2869   1.0000
  15.500   2.0670   0.07797   0.07185  -0.1693   0.2816   1.0000
  15.750   2.0750   0.07949   0.07333  -0.1687   0.2767   1.0000
  16.000   2.0528   0.08489   0.07893  -0.1677   0.2709   1.0000
  16.250   2.0320   0.09036   0.08456  -0.1671   0.2643   1.0000
  16.500   2.0417   0.09177   0.08588  -0.1667   0.2587   1.0000
  16.750   1.9988   0.10062   0.09504  -0.1667   0.2502   1.0000
  17.000   2.0051   0.10257   0.09689  -0.1665   0.2437   1.0000
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