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GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 6K AIRFOIL (goe06k-il)
Reynolds number: 500,000
Max Cl/Cd: 116.52 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe06k-il-500000-n5.txt
Download as CSV file: xf-goe06k-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 6K 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3347   0.08452   0.08222  -0.0653   0.9806   0.0067
  -8.000  -0.3239   0.07978   0.07750  -0.0708   0.9786   0.0067
  -7.750  -0.3225   0.07681   0.07453  -0.0724   0.9722   0.0067
  -6.750  -0.2223   0.03835   0.03606  -0.0924   0.9481   0.0067
  -6.250  -0.2428   0.04767   0.04501  -0.0972   0.9456   0.0045
  -6.000  -0.2220   0.04208   0.03922  -0.1000   0.9432   0.0045
  -5.750  -0.1986   0.03913   0.03613  -0.1021   0.9418   0.0057
  -5.500  -0.1893   0.03494   0.03171  -0.1001   0.9348   0.0052
  -5.250  -0.1681   0.03130   0.02781  -0.1002   0.9319   0.0057
  -5.000  -0.1462   0.02641   0.02252  -0.0997   0.9297   0.0054
  -4.500  -0.1124   0.01573   0.01046  -0.0939   0.9229   0.0047
  -4.250  -0.0894   0.01387   0.00822  -0.0929   0.9200   0.0051
  -4.000  -0.0616   0.01272   0.00683  -0.0930   0.9180   0.0056
  -3.750  -0.0323   0.01176   0.00565  -0.0933   0.9165   0.0063
  -3.500  -0.0020   0.01096   0.00470  -0.0940   0.9152   0.0073
  -3.250   0.0300   0.01030   0.00394  -0.0951   0.9140   0.0084
  -3.000   0.0584   0.00983   0.00340  -0.0954   0.9119   0.0102
  -2.750   0.0783   0.00953   0.00304  -0.0937   0.9074   0.0120
  -2.500   0.1060   0.00916   0.00261  -0.0938   0.9046   0.0156
  -2.250   0.1364   0.00886   0.00229  -0.0946   0.9025   0.0260
  -2.000   0.1683   0.00863   0.00211  -0.0957   0.9007   0.0493
  -1.750   0.2015   0.00845   0.00192  -0.0972   0.8992   0.0638
  -1.500   0.2250   0.00830   0.00182  -0.0964   0.8956   0.0864
  -1.250   0.2452   0.00784   0.00174  -0.0951   0.8913   0.2218
  -1.000   0.2696   0.00736   0.00167  -0.0948   0.8880   0.3711
  -0.750   0.2919   0.00664   0.00163  -0.0940   0.8852   0.6038
  -0.500   0.3969   0.00594   0.00194  -0.1121   0.8911   0.9385
  -0.250   0.4365   0.00603   0.00200  -0.1149   0.8892   0.9634
   0.000   0.4758   0.00614   0.00208  -0.1176   0.8875   0.9838
   0.250   0.5336   0.00621   0.00215  -0.1248   0.8875   0.9961
   0.500   0.5843   0.00614   0.00207  -0.1303   0.8836   1.0000
   0.750   0.6043   0.00614   0.00206  -0.1286   0.8731   1.0000
   1.000   0.6292   0.00615   0.00207  -0.1280   0.8656   1.0000
   1.250   0.6539   0.00615   0.00208  -0.1275   0.8577   1.0000
   1.500   0.6757   0.00617   0.00210  -0.1261   0.8460   1.0000
   1.750   0.6987   0.00617   0.00208  -0.1250   0.8274   1.0000
   2.000   0.7180   0.00622   0.00207  -0.1230   0.7997   1.0000
   2.250   0.7376   0.00633   0.00208  -0.1211   0.7678   1.0000
   2.500   0.7506   0.00660   0.00214  -0.1176   0.7140   1.0000
   2.750   0.7411   0.00740   0.00233  -0.1091   0.5808   1.0000
   3.000   0.7280   0.00860   0.00277  -0.1004   0.4252   1.0000
   3.250   0.7232   0.00988   0.00325  -0.0938   0.2498   1.0000
   3.500   0.7287   0.01086   0.00368  -0.0895   0.1243   1.0000
   3.750   0.7406   0.01155   0.00408  -0.0864   0.0571   1.0000
   4.000   0.7554   0.01211   0.00446  -0.0838   0.0175   1.0000
   4.250   0.7727   0.01251   0.00489  -0.0817   0.0120   1.0000
   4.500   0.7894   0.01294   0.00536  -0.0794   0.0090   1.0000
   4.750   0.8058   0.01339   0.00586  -0.0771   0.0074   1.0000
   5.000   0.8218   0.01390   0.00644  -0.0747   0.0066   1.0000
   5.250   0.8377   0.01442   0.00702  -0.0723   0.0057   1.0000
   5.500   0.8531   0.01503   0.00768  -0.0699   0.0050   1.0000
   5.750   0.8685   0.01570   0.00846  -0.0674   0.0046   1.0000
   6.000   0.8835   0.01658   0.00944  -0.0649   0.0043   1.0000
   6.250   0.9008   0.01747   0.01042  -0.0629   0.0040   1.0000
   6.500   0.9201   0.01859   0.01164  -0.0614   0.0037   1.0000
   6.750   0.9480   0.02050   0.01373  -0.0618   0.0036   1.0000
   7.000   0.9791   0.02295   0.01659  -0.0622   0.0034   1.0000
   7.250   1.0020   0.02447   0.01842  -0.0612   0.0027   1.0000
   7.500   1.0238   0.02787   0.02227  -0.0598   0.0026   1.0000
   7.750   1.0376   0.03111   0.02591  -0.0569   0.0026   1.0000
   8.000   1.0429   0.03655   0.03190  -0.0519   0.0026   1.0000
   8.250   1.0445   0.04069   0.03640  -0.0470   0.0026   1.0000
   8.500   1.0385   0.04634   0.04246  -0.0407   0.0028   1.0000
   8.750   1.0317   0.05062   0.04702  -0.0352   0.0029   1.0000
   9.000   1.0223   0.05456   0.05120  -0.0298   0.0029   1.0000
   9.250   1.0111   0.05792   0.05475  -0.0246   0.0030   1.0000
   9.500   0.9939   0.06104   0.05803  -0.0188   0.0031   1.0000
   9.750   0.9767   0.06426   0.06140  -0.0139   0.0032   1.0000
  10.000   0.9620   0.06702   0.06427  -0.0104   0.0033   1.0000
  10.250   0.9429   0.07065   0.06803  -0.0073   0.0033   1.0000
  10.500   0.9227   0.07475   0.07225  -0.0055   0.0033   1.0000
  10.750   0.9038   0.07923   0.07683  -0.0050   0.0033   1.0000
  11.000   0.8838   0.08474   0.08244  -0.0063   0.0033   1.0000
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