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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 500,000
Max Cl/Cd: 101.84 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe408-il-500000.txt
Download as CSV file: xf-goe408-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3196   0.09191   0.08983  -0.0229   1.0000   0.0220
  -8.500  -0.3254   0.08873   0.08668  -0.0240   1.0000   0.0221
  -8.250  -0.3284   0.08534   0.08331  -0.0243   1.0000   0.0221
  -8.000  -0.3292   0.08048   0.07849  -0.0230   1.0000   0.0224
  -7.750  -0.3281   0.07753   0.07555  -0.0220   1.0000   0.0226
  -7.500  -0.3309   0.07474   0.07279  -0.0211   1.0000   0.0228
  -7.250  -0.3364   0.07225   0.07033  -0.0198   1.0000   0.0230
  -7.000  -0.4282   0.08094   0.07890  -0.0195   1.0000   0.0225
  -6.750  -0.4262   0.07805   0.07602  -0.0191   1.0000   0.0226
  -6.500  -0.4245   0.07535   0.07333  -0.0183   1.0000   0.0228
  -6.250  -0.4000   0.07184   0.06980  -0.0224   0.9974   0.0235
  -6.000  -0.3700   0.06730   0.06520  -0.0291   0.9940   0.0241
  -5.750  -0.3266   0.06097   0.05869  -0.0402   0.9883   0.0276
  -5.250  -0.2617   0.04988   0.04725  -0.0505   0.9786   0.0279
  -4.750  -0.2167   0.03958   0.03665  -0.0550   0.9673   0.0290
  -4.500  -0.1873   0.03675   0.03369  -0.0569   0.9634   0.0297
  -4.250  -0.1742   0.02865   0.02502  -0.0545   0.9526   0.0290
  -4.000  -0.1440   0.03055   0.02710  -0.0557   0.9452   0.0319
  -3.750  -0.1215   0.02544   0.02152  -0.0543   0.9377   0.0333
  -3.500  -0.0964   0.02601   0.02217  -0.0545   0.9264   0.0388
  -3.250  -0.0716   0.02371   0.01961  -0.0534   0.9161   0.0421
  -3.000  -0.0439   0.02073   0.01624  -0.0531   0.9084   0.0468
  -2.750  -0.0066   0.02000   0.01549  -0.0556   0.8993   0.0502
  -2.500   0.0323   0.01788   0.01288  -0.0574   0.8891   0.0579
  -2.250   0.0803   0.01664   0.01159  -0.0623   0.8776   0.0609
  -2.000   0.1302   0.01558   0.01018  -0.0671   0.8612   0.0712
  -1.750   0.1778   0.01290   0.00691  -0.0703   0.8418   0.0574
  -1.500   0.2233   0.01203   0.00580  -0.0742   0.8195   0.0573
  -1.250   0.2565   0.01146   0.00503  -0.0753   0.7961   0.0572
  -1.000   0.2863   0.01098   0.00439  -0.0756   0.7763   0.0574
  -0.750   0.3130   0.01056   0.00385  -0.0752   0.7586   0.0577
  -0.500   0.3385   0.01021   0.00342  -0.0746   0.7423   0.0586
  -0.250   0.3631   0.00999   0.00314  -0.0738   0.7275   0.0603
   0.000   0.3873   0.00980   0.00289  -0.0729   0.7139   0.0614
   0.500   0.4341   0.00953   0.00251  -0.0706   0.6882   0.0639
   0.750   0.4570   0.00942   0.00237  -0.0694   0.6758   0.0651
   1.000   0.4797   0.00935   0.00226  -0.0681   0.6629   0.0662
   1.250   0.5017   0.00931   0.00216  -0.0667   0.6480   0.0676
   1.500   0.5234   0.00930   0.00209  -0.0652   0.6321   0.0688
   1.750   0.5452   0.00921   0.00199  -0.0637   0.6170   0.0738
   2.000   0.5668   0.00923   0.00196  -0.0622   0.5999   0.0776
   2.250   0.5884   0.00926   0.00194  -0.0607   0.5822   0.0840
   2.500   0.6100   0.00927   0.00197  -0.0593   0.5639   0.1103
   2.750   0.8326   0.00839   0.00289  -0.1056   0.5161   1.0000
   3.000   0.8555   0.00856   0.00299  -0.1045   0.4992   1.0000
   3.250   0.8782   0.00873   0.00309  -0.1033   0.4817   1.0000
   3.500   0.9001   0.00895   0.00321  -0.1020   0.4619   1.0000
   3.750   0.9230   0.00914   0.00334  -0.1009   0.4463   1.0000
   4.000   0.9457   0.00933   0.00349  -0.0998   0.4307   1.0000
   4.250   0.9684   0.00953   0.00364  -0.0987   0.4144   1.0000
   4.500   0.9907   0.00974   0.00380  -0.0975   0.3961   1.0000
   4.750   1.0133   0.00995   0.00398  -0.0964   0.3811   1.0000
   5.000   1.0353   0.01018   0.00417  -0.0952   0.3620   1.0000
   5.250   1.0569   0.01044   0.00437  -0.0939   0.3425   1.0000
   5.500   1.0781   0.01072   0.00459  -0.0926   0.3177   1.0000
   5.750   1.0975   0.01113   0.00484  -0.0909   0.2833   1.0000
   6.000   1.1147   0.01169   0.00519  -0.0889   0.2372   1.0000
   6.250   1.1324   0.01224   0.00556  -0.0870   0.2022   1.0000
   6.500   1.1507   0.01273   0.00594  -0.0852   0.1779   1.0000
   6.750   1.1696   0.01317   0.00632  -0.0835   0.1604   1.0000
   7.000   1.1888   0.01358   0.00670  -0.0819   0.1461   1.0000
   7.250   1.2067   0.01408   0.00712  -0.0800   0.1263   1.0000
   7.500   1.2237   0.01463   0.00756  -0.0780   0.1023   1.0000
   7.750   1.2334   0.01567   0.00829  -0.0747   0.0567   1.0000
   8.000   1.2460   0.01650   0.00910  -0.0719   0.0421   1.0000
   8.250   1.2597   0.01723   0.00982  -0.0692   0.0319   1.0000
   8.500   1.2726   0.01800   0.01058  -0.0664   0.0250   1.0000
   8.750   1.2866   0.01864   0.01130  -0.0638   0.0226   1.0000
   9.000   1.2991   0.01927   0.01197  -0.0609   0.0204   1.0000
   9.250   1.3063   0.02006   0.01283  -0.0571   0.0191   1.0000
   9.500   1.3100   0.02102   0.01389  -0.0526   0.0177   1.0000
   9.750   1.3194   0.02169   0.01465  -0.0493   0.0169   1.0000
  10.000   1.3280   0.02244   0.01550  -0.0460   0.0160   1.0000
  10.250   1.3357   0.02325   0.01638  -0.0427   0.0153   1.0000
  10.500   1.3396   0.02433   0.01752  -0.0389   0.0144   1.0000
  10.750   1.3401   0.02565   0.01894  -0.0348   0.0140   1.0000
  11.000   1.3313   0.02772   0.02115  -0.0297   0.0135   1.0000
  11.250   1.3339   0.02913   0.02267  -0.0264   0.0133   1.0000
  11.500   1.3393   0.03041   0.02406  -0.0238   0.0129   1.0000
  11.750   1.3406   0.03212   0.02590  -0.0209   0.0128   1.0000
  12.000   1.3450   0.03363   0.02752  -0.0187   0.0124   1.0000
  12.250   1.3476   0.03538   0.02940  -0.0166   0.0121   1.0000
  12.500   1.3498   0.03726   0.03139  -0.0147   0.0115   1.0000
  12.750   1.3499   0.03953   0.03378  -0.0128   0.0114   1.0000
  13.000   1.3538   0.04128   0.03562  -0.0119   0.0110   1.0000
  13.250   1.3543   0.04359   0.03803  -0.0108   0.0107   1.0000
  13.500   1.3512   0.04647   0.04102  -0.0096   0.0105   1.0000
  13.750   1.3507   0.04904   0.04367  -0.0090   0.0102   1.0000
  14.000   1.3459   0.05233   0.04709  -0.0080   0.0101   1.0000
  14.250   1.3365   0.05636   0.05128  -0.0070   0.0098   1.0000
  14.500   1.3373   0.05899   0.05404  -0.0071   0.0100   1.0000
  14.750   1.3175   0.06475   0.06004  -0.0063   0.0097   1.0000
  15.000   1.3076   0.06905   0.06452  -0.0070   0.0096   1.0000
  15.250   1.2967   0.07369   0.06933  -0.0080   0.0096   1.0000
  15.750   1.2732   0.08380   0.07979  -0.0113   0.0095   1.0000
  16.000   1.2612   0.08924   0.08539  -0.0135   0.0095   1.0000
  16.250   1.2411   0.09615   0.09247  -0.0157   0.0096   1.0000
  16.500   1.2273   0.10233   0.09880  -0.0185   0.0096   1.0000
  17.000   1.1922   0.11701   0.11380  -0.0260   0.0096   1.0000
  17.250   1.1782   0.12448   0.12144  -0.0306   0.0094   1.0000
  17.500   1.1524   0.13392   0.13101  -0.0351   0.0097   1.0000
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