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GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 622 AIRFOIL (goe622-il)
Reynolds number: 100,000
Max Cl/Cd: 52.85 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe622-il-100000-n5.txt
Download as CSV file: xf-goe622-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 622 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4874   0.09042   0.08557  -0.0182   1.0000   0.0229
  -8.250  -0.4880   0.08613   0.08134  -0.0206   1.0000   0.0227
  -8.000  -0.4901   0.08177   0.07705  -0.0232   1.0000   0.0225
  -7.750  -0.4905   0.07686   0.07221  -0.0273   1.0000   0.0223
  -7.500  -0.4885   0.07135   0.06671  -0.0321   1.0000   0.0222
  -7.250  -0.4853   0.06540   0.06074  -0.0368   1.0000   0.0222
  -7.000  -0.4809   0.05910   0.05435  -0.0408   1.0000   0.0222
  -6.750  -0.4755   0.05262   0.04770  -0.0438   1.0000   0.0225
  -6.500  -0.4690   0.04600   0.04077  -0.0455   1.0000   0.0229
  -6.250  -0.4603   0.03970   0.03397  -0.0462   1.0000   0.0234
  -6.000  -0.4480   0.03436   0.02798  -0.0460   1.0000   0.0240
  -5.750  -0.4319   0.03013   0.02306  -0.0453   1.0000   0.0245
  -5.500  -0.4127   0.02699   0.01926  -0.0442   1.0000   0.0253
  -5.250  -0.3932   0.02480   0.01685  -0.0435   1.0000   0.0272
  -5.000  -0.3721   0.02362   0.01545  -0.0426   1.0000   0.0307
  -4.750  -0.3493   0.02184   0.01327  -0.0416   1.0000   0.0339
  -4.500  -0.3269   0.02041   0.01169  -0.0408   1.0000   0.0379
  -4.250  -0.3038   0.01955   0.01059  -0.0400   1.0000   0.0453
  -4.000  -0.2807   0.01852   0.00954  -0.0394   1.0000   0.0536
  -3.750  -0.2573   0.01791   0.00887  -0.0388   1.0000   0.0657
  -3.500  -0.2330   0.01753   0.00843  -0.0384   0.9996   0.0806
  -3.250  -0.1961   0.01687   0.00764  -0.0404   0.9948   0.0971
  -3.000  -0.1602   0.01633   0.00707  -0.0423   0.9889   0.1179
  -2.750  -0.1245   0.01586   0.00657  -0.0442   0.9829   0.1403
  -2.500  -0.0877   0.01541   0.00616  -0.0463   0.9771   0.1649
  -2.250  -0.0535   0.01499   0.00581  -0.0479   0.9697   0.1972
  -2.000  -0.0178   0.01447   0.00551  -0.0499   0.9632   0.2540
  -1.750   0.0163   0.01371   0.00528  -0.0515   0.9562   0.3908
  -1.500   0.0463   0.01267   0.00520  -0.0518   0.9499   0.6487
  -1.250   0.0864   0.01207   0.00516  -0.0527   0.9445   0.9341
  -1.000   0.1329   0.01199   0.00487  -0.0566   0.9378   1.0000
  -0.750   0.1672   0.01198   0.00471  -0.0579   0.9275   1.0000
  -0.500   0.2008   0.01198   0.00457  -0.0590   0.9168   1.0000
  -0.250   0.2346   0.01198   0.00444  -0.0601   0.9062   1.0000
   0.000   0.2684   0.01197   0.00433  -0.0612   0.8955   1.0000
   0.250   0.2997   0.01199   0.00426  -0.0617   0.8831   1.0000
   0.500   0.3294   0.01202   0.00422  -0.0619   0.8694   1.0000
   0.750   0.3584   0.01205   0.00419  -0.0618   0.8551   1.0000
   1.000   0.3861   0.01209   0.00419  -0.0615   0.8392   1.0000
   1.250   0.4126   0.01213   0.00418  -0.0609   0.8195   1.0000
   1.500   0.4396   0.01213   0.00411  -0.0602   0.7982   1.0000
   1.750   0.4651   0.01218   0.00412  -0.0594   0.7738   1.0000
   2.000   0.4914   0.01224   0.00413  -0.0587   0.7520   1.0000
   2.250   0.5173   0.01233   0.00417  -0.0579   0.7293   1.0000
   2.500   0.5431   0.01244   0.00424  -0.0572   0.7053   1.0000
   2.750   0.5689   0.01257   0.00430  -0.0564   0.6809   1.0000
   3.000   0.5944   0.01274   0.00439  -0.0556   0.6555   1.0000
   3.250   0.6197   0.01295   0.00457  -0.0548   0.6300   1.0000
   3.500   0.6449   0.01319   0.00476  -0.0541   0.6055   1.0000
   3.750   0.6701   0.01345   0.00498  -0.0533   0.5811   1.0000
   4.000   0.6950   0.01372   0.00524  -0.0526   0.5560   1.0000
   4.250   0.7201   0.01400   0.00558  -0.0520   0.5322   1.0000
   4.500   0.7449   0.01431   0.00590  -0.0513   0.5065   1.0000
   4.750   0.7692   0.01463   0.00625  -0.0505   0.4756   1.0000
   5.000   0.7928   0.01500   0.00660  -0.0496   0.4358   1.0000
   5.250   0.8155   0.01547   0.00701  -0.0486   0.3872   1.0000
   5.500   0.8355   0.01622   0.00744  -0.0473   0.3234   1.0000
   5.750   0.8544   0.01720   0.00804  -0.0461   0.2551   1.0000
   6.000   0.8752   0.01804   0.00870  -0.0452   0.2091   1.0000
   6.250   0.8968   0.01883   0.00939  -0.0444   0.1683   1.0000
   6.500   0.9164   0.01987   0.01023  -0.0434   0.1242   1.0000
   6.750   0.9359   0.02100   0.01116  -0.0424   0.0674   1.0000
   7.000   0.9529   0.02256   0.01247  -0.0409   0.0368   1.0000
   7.250   0.9715   0.02386   0.01378  -0.0396   0.0276   1.0000
   7.500   0.9902   0.02512   0.01517  -0.0383   0.0238   1.0000
   7.750   1.0067   0.02661   0.01682  -0.0367   0.0218   1.0000
   8.000   1.0212   0.02830   0.01868  -0.0349   0.0207   1.0000
   8.250   1.0370   0.02981   0.02043  -0.0332   0.0196   1.0000
   8.500   1.0522   0.03144   0.02228  -0.0316   0.0182   1.0000
   8.750   1.0670   0.03327   0.02441  -0.0299   0.0172   1.0000
   9.000   1.0815   0.03536   0.02673  -0.0282   0.0167   1.0000
   9.250   1.0958   0.03768   0.02931  -0.0265   0.0163   1.0000
   9.500   1.1088   0.04025   0.03217  -0.0248   0.0159   1.0000
   9.750   1.1190   0.04308   0.03534  -0.0230   0.0156   1.0000
  10.000   1.1255   0.04607   0.03868  -0.0210   0.0154   1.0000
  10.250   1.1274   0.04911   0.04206  -0.0188   0.0151   1.0000
  10.500   1.1233   0.05205   0.04531  -0.0163   0.0148   1.0000
  10.750   1.1156   0.05516   0.04871  -0.0140   0.0145   1.0000
  11.000   1.1051   0.05860   0.05242  -0.0124   0.0143   1.0000
  11.250   1.0921   0.06250   0.05659  -0.0118   0.0142   1.0000
  11.500   1.0771   0.06701   0.06135  -0.0123   0.0141   1.0000
  11.750   1.0600   0.07236   0.06695  -0.0140   0.0142   1.0000
  12.000   1.0410   0.07868   0.07350  -0.0172   0.0143   1.0000
  12.250   1.0191   0.08647   0.08152  -0.0220   0.0147   1.0000
  12.500   0.9933   0.09624   0.09149  -0.0286   0.0152   1.0000
  12.750   0.9633   0.10879   0.10420  -0.0372   0.0160   1.0000
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