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GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 412 AIRFOIL (goe412-il)
Reynolds number: 200,000
Max Cl/Cd: 82.91 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe412-il-200000.txt
Download as CSV file: xf-goe412-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 412 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2137   0.09917   0.09566  -0.0686   0.9783   0.0707
  -9.000  -0.2220   0.09283   0.08934  -0.0879   0.9683   0.0743
  -8.750  -0.2046   0.08759   0.08410  -0.0877   0.9651   0.0752
  -8.500  -0.1753   0.08496   0.08144  -0.0869   0.9637   0.0767
  -8.250  -0.1515   0.08181   0.07826  -0.0898   0.9603   0.0788
  -8.000  -0.1317   0.07770   0.07414  -0.0956   0.9566   0.0816
  -7.750  -0.1596   0.06794   0.06413  -0.1185   0.9312   0.0867
  -7.500  -0.1373   0.06449   0.06080  -0.1168   0.9289   0.0877
  -7.250  -0.1217   0.06247   0.05878  -0.1154   0.9224   0.0886
  -7.000  -0.1058   0.06018   0.05648  -0.1153   0.9157   0.0899
  -6.750  -0.0873   0.05714   0.05337  -0.1175   0.9111   0.0922
  -6.500  -0.0894   0.04957   0.04524  -0.1259   0.8984   0.1008
  -6.250  -0.1033   0.03255   0.02695  -0.1268   0.8880   0.0626
  -6.000  -0.0820   0.02919   0.02322  -0.1269   0.8836   0.0613
  -5.750  -0.0605   0.02642   0.02001  -0.1266   0.8787   0.0605
  -5.500  -0.0391   0.02443   0.01765  -0.1257   0.8720   0.0603
  -5.250  -0.0114   0.02283   0.01571  -0.1257   0.8681   0.0612
  -5.000   0.0155   0.02167   0.01425  -0.1255   0.8634   0.0624
  -4.750   0.0403   0.02072   0.01307  -0.1249   0.8570   0.0631
  -4.500   0.0693   0.01971   0.01185  -0.1249   0.8528   0.0639
  -4.250   0.0974   0.01854   0.01063  -0.1249   0.8487   0.0655
  -4.000   0.1218   0.01802   0.01011  -0.1243   0.8419   0.0674
  -3.750   0.1505   0.01742   0.00945  -0.1242   0.8374   0.0700
  -3.500   0.1801   0.01697   0.00886  -0.1243   0.8334   0.0739
  -3.250   0.2035   0.01648   0.00846  -0.1236   0.8264   0.0790
  -3.000   0.2319   0.01606   0.00797  -0.1235   0.8216   0.0867
  -2.750   0.2605   0.01545   0.00747  -0.1235   0.8177   0.1068
  -2.500   0.2846   0.01535   0.00745  -0.1229   0.8105   0.1333
  -2.250   0.3127   0.01516   0.00725  -0.1229   0.8056   0.1530
  -2.000   0.3425   0.01490   0.00698  -0.1231   0.8018   0.1726
  -1.750   0.3658   0.01483   0.00701  -0.1225   0.7945   0.1928
  -1.500   0.3932   0.01458   0.00689  -0.1224   0.7894   0.2222
  -1.250   0.4225   0.01430   0.00677  -0.1226   0.7855   0.2803
  -1.000   0.4448   0.01412   0.00691  -0.1219   0.7784   0.3594
  -0.750   0.4678   0.01349   0.00692  -0.1210   0.7731   0.5309
  -0.500   0.5356   0.01240   0.00685  -0.1280   0.7701   0.9935
  -0.250   0.5659   0.01255   0.00690  -0.1287   0.7635   1.0000
   0.000   0.5911   0.01263   0.00684  -0.1281   0.7573   1.0000
   0.250   0.6193   0.01263   0.00668  -0.1279   0.7520   1.0000
   0.500   0.6411   0.01274   0.00673  -0.1267   0.7431   1.0000
   0.750   0.6695   0.01269   0.00653  -0.1265   0.7371   1.0000
   1.000   0.6920   0.01282   0.00662  -0.1254   0.7290   1.0000
   1.250   0.7191   0.01281   0.00650  -0.1250   0.7226   1.0000
   1.500   0.7440   0.01290   0.00654  -0.1244   0.7156   1.0000
   1.750   0.7693   0.01296   0.00654  -0.1238   0.7085   1.0000
   2.000   0.7981   0.01299   0.00645  -0.1238   0.7033   1.0000
   2.250   0.8204   0.01315   0.00663  -0.1228   0.6953   1.0000
   2.500   0.8485   0.01316   0.00656  -0.1226   0.6893   1.0000
   2.750   0.8724   0.01330   0.00669  -0.1219   0.6817   1.0000
   3.000   0.8991   0.01332   0.00666  -0.1215   0.6745   1.0000
   3.250   0.9240   0.01341   0.00672  -0.1209   0.6666   1.0000
   3.500   0.9501   0.01344   0.00672  -0.1204   0.6586   1.0000
   3.750   0.9751   0.01355   0.00682  -0.1198   0.6508   1.0000
   4.000   1.0008   0.01363   0.00687  -0.1193   0.6430   1.0000
   4.250   1.0258   0.01374   0.00698  -0.1187   0.6349   1.0000
   4.500   1.0512   0.01379   0.00701  -0.1182   0.6259   1.0000
   4.750   1.0746   0.01391   0.00715  -0.1173   0.6161   1.0000
   5.000   1.1016   0.01397   0.00714  -0.1170   0.6076   1.0000
   5.250   1.1230   0.01411   0.00734  -0.1158   0.5962   1.0000
   5.500   1.1468   0.01425   0.00748  -0.1150   0.5861   1.0000
   5.750   1.1716   0.01437   0.00754  -0.1144   0.5756   1.0000
   6.000   1.1926   0.01453   0.00774  -0.1131   0.5625   1.0000
   6.250   1.2137   0.01470   0.00792  -0.1118   0.5489   1.0000
   6.500   1.2346   0.01491   0.00812  -0.1105   0.5350   1.0000
   6.750   1.2552   0.01514   0.00836  -0.1091   0.5210   1.0000
   7.000   1.2751   0.01541   0.00861  -0.1077   0.5066   1.0000
   7.250   1.2941   0.01571   0.00890  -0.1061   0.4919   1.0000
   7.500   1.3120   0.01605   0.00923  -0.1044   0.4765   1.0000
   7.750   1.3287   0.01643   0.00959  -0.1025   0.4605   1.0000
   8.000   1.3439   0.01686   0.01000  -0.1003   0.4439   1.0000
   8.250   1.3570   0.01733   0.01044  -0.0978   0.4268   1.0000
   8.500   1.3673   0.01786   0.01093  -0.0948   0.4095   1.0000
   8.750   1.3765   0.01850   0.01152  -0.0918   0.3915   1.0000
   9.000   1.3840   0.01925   0.01219  -0.0886   0.3725   1.0000
   9.250   1.3908   0.02010   0.01297  -0.0855   0.3534   1.0000
   9.500   1.3976   0.02101   0.01383  -0.0825   0.3344   1.0000
   9.750   1.4041   0.02200   0.01478  -0.0797   0.3162   1.0000
  10.000   1.4108   0.02306   0.01580  -0.0771   0.2996   1.0000
  10.250   1.4181   0.02415   0.01687  -0.0747   0.2847   1.0000
  10.500   1.4257   0.02528   0.01798  -0.0724   0.2715   1.0000
  10.750   1.4330   0.02649   0.01916  -0.0702   0.2596   1.0000
  11.000   1.4413   0.02767   0.02036  -0.0683   0.2482   1.0000
  11.250   1.4502   0.02886   0.02160  -0.0666   0.2379   1.0000
  11.500   1.4571   0.03023   0.02296  -0.0648   0.2281   1.0000
  11.750   1.4633   0.03167   0.02441  -0.0630   0.2178   1.0000
  12.000   1.4702   0.03313   0.02591  -0.0614   0.2073   1.0000
  12.250   1.4750   0.03477   0.02757  -0.0598   0.1976   1.0000
  12.500   1.4783   0.03658   0.02938  -0.0581   0.1881   1.0000
  12.750   1.4844   0.03822   0.03110  -0.0568   0.1787   1.0000
  13.000   1.4868   0.04022   0.03312  -0.0553   0.1695   1.0000
  13.250   1.4883   0.04238   0.03531  -0.0539   0.1587   1.0000
  13.500   1.4905   0.04458   0.03757  -0.0527   0.1447   1.0000
  13.750   1.4916   0.04701   0.04002  -0.0518   0.1163   1.0000
  14.000   1.4757   0.05118   0.04389  -0.0503   0.0870   1.0000
  14.250   1.4599   0.05548   0.04811  -0.0489   0.0735   1.0000
  14.500   1.4467   0.05970   0.05235  -0.0478   0.0613   1.0000
  14.750   1.4376   0.06366   0.05631  -0.0470   0.0516   1.0000
  15.000   1.4314   0.06738   0.06007  -0.0466   0.0457   1.0000
  15.250   1.4233   0.07145   0.06420  -0.0463   0.0425   1.0000
  15.500   1.4173   0.07536   0.06820  -0.0463   0.0399   1.0000
  15.750   1.4087   0.07970   0.07260  -0.0464   0.0381   1.0000
  16.000   1.3981   0.08436   0.07733  -0.0467   0.0367   1.0000
  16.250   1.3930   0.08836   0.08146  -0.0471   0.0354   1.0000
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