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GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 AIRFOIL (goe602-il)
Reynolds number: 500,000
Max Cl/Cd: 102.17 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602-il-500000.txt
Download as CSV file: xf-goe602-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 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  -0.4034   0.08842   0.08631  -0.0338   1.0000   0.0214
  -8.500  -0.4141   0.08626   0.08420  -0.0321   1.0000   0.0215
  -8.250  -0.4227   0.08389   0.08187  -0.0313   0.9997   0.0220
  -8.000  -0.4105   0.07878   0.07676  -0.0379   0.9963   0.0227
  -7.750  -0.3992   0.07261   0.07059  -0.0471   0.9909   0.0237
  -7.500  -0.3675   0.05933   0.05716  -0.0693   0.9847   0.0258
  -7.250  -0.3826   0.03812   0.03528  -0.0822   0.9743   0.0188
  -7.000  -0.3638   0.02940   0.02578  -0.0866   0.9712   0.0190
  -6.750  -0.3475   0.02591   0.02175  -0.0860   0.9644   0.0194
  -6.500  -0.3252   0.02095   0.01616  -0.0872   0.9611   0.0203
  -6.250  -0.2920   0.01969   0.01478  -0.0890   0.9595   0.0213
  -6.000  -0.2567   0.01870   0.01366  -0.0910   0.9583   0.0227
  -5.750  -0.2194   0.01801   0.01280  -0.0930   0.9574   0.0250
  -5.500  -0.1955   0.01773   0.01234  -0.0921   0.9510   0.0260
  -5.250  -0.1655   0.01491   0.00926  -0.0932   0.9485   0.0281
  -5.000  -0.1303   0.01420   0.00851  -0.0948   0.9463   0.0303
  -4.750  -0.0941   0.01354   0.00776  -0.0966   0.9443   0.0328
  -4.500  -0.0663   0.01302   0.00714  -0.0964   0.9388   0.0343
  -4.250  -0.0374   0.01196   0.00598  -0.0966   0.9340   0.0361
  -4.000  -0.0054   0.01111   0.00511  -0.0976   0.9305   0.0390
  -3.750   0.0209   0.01067   0.00462  -0.0971   0.9242   0.0411
  -3.500   0.0501   0.01026   0.00416  -0.0973   0.9185   0.0433
  -3.250   0.0802   0.00992   0.00376  -0.0977   0.9134   0.0452
  -3.000   0.1057   0.00955   0.00334  -0.0971   0.9055   0.0469
  -2.750   0.1352   0.00914   0.00288  -0.0973   0.8998   0.0512
  -2.500   0.1605   0.00892   0.00264  -0.0966   0.8911   0.0564
  -2.250   0.1885   0.00861   0.00238  -0.0965   0.8840   0.0754
  -2.000   0.2121   0.00798   0.00217  -0.0958   0.8748   0.1933
  -1.750   0.2369   0.00755   0.00208  -0.0954   0.8657   0.3161
  -1.500   0.2636   0.00726   0.00197  -0.0951   0.8571   0.3872
  -1.250   0.2864   0.00685   0.00192  -0.0941   0.8460   0.5019
  -1.000   0.3085   0.00644   0.00191  -0.0929   0.8350   0.6406
  -0.750   0.3312   0.00615   0.00188  -0.0915   0.8235   0.7355
  -0.500   0.3525   0.00585   0.00191  -0.0896   0.8116   0.8480
  -0.250   0.3883   0.00576   0.00191  -0.0908   0.7993   0.9396
   0.000   0.4454   0.00579   0.00187  -0.0969   0.7861   0.9790
   0.250   0.4934   0.00585   0.00181  -0.1012   0.7683   0.9951
   0.500   0.5269   0.00592   0.00176  -0.1025   0.7472   1.0000
   0.750   0.5478   0.00603   0.00173  -0.1010   0.7252   1.0000
   1.000   0.5692   0.00615   0.00173  -0.0995   0.7047   1.0000
   1.250   0.5909   0.00628   0.00175  -0.0982   0.6861   1.0000
   1.500   0.6128   0.00641   0.00179  -0.0969   0.6675   1.0000
   1.750   0.6350   0.00655   0.00184  -0.0957   0.6490   1.0000
   2.000   0.6570   0.00670   0.00190  -0.0944   0.6299   1.0000
   2.250   0.6790   0.00687   0.00198  -0.0932   0.6113   1.0000
   2.500   0.7011   0.00704   0.00206  -0.0920   0.5901   1.0000
   2.750   0.7229   0.00724   0.00215  -0.0907   0.5691   1.0000
   3.000   0.7456   0.00741   0.00226  -0.0896   0.5503   1.0000
   3.250   0.7687   0.00759   0.00238  -0.0886   0.5332   1.0000
   3.500   0.7918   0.00778   0.00251  -0.0877   0.5160   1.0000
   3.750   0.8148   0.00798   0.00265  -0.0867   0.4988   1.0000
   4.000   0.8378   0.00820   0.00282  -0.0857   0.4816   1.0000
   4.250   0.8602   0.00843   0.00298  -0.0847   0.4581   1.0000
   4.500   0.8814   0.00875   0.00316  -0.0834   0.4278   1.0000
   4.750   0.9034   0.00903   0.00335  -0.0823   0.4029   1.0000
   5.000   0.9247   0.00937   0.00357  -0.0811   0.3715   1.0000
   5.250   0.9453   0.00977   0.00382  -0.0798   0.3371   1.0000
   5.500   0.9652   0.01024   0.00410  -0.0785   0.2958   1.0000
   5.750   0.9835   0.01084   0.00446  -0.0769   0.2478   1.0000
   6.000   0.9991   0.01168   0.00495  -0.0749   0.1842   1.0000
   6.250   1.0079   0.01307   0.00577  -0.0719   0.0906   1.0000
   6.500   1.0196   0.01424   0.00658  -0.0693   0.0308   1.0000
   6.750   1.0379   0.01489   0.00729  -0.0675   0.0247   1.0000
   7.000   1.0580   0.01537   0.00785  -0.0661   0.0231   1.0000
   7.250   1.0765   0.01594   0.00849  -0.0645   0.0211   1.0000
   7.500   1.0923   0.01668   0.00930  -0.0625   0.0194   1.0000
   7.750   1.1001   0.01785   0.01059  -0.0591   0.0180   1.0000
   8.000   1.1129   0.01855   0.01136  -0.0565   0.0175   1.0000
   8.250   1.1254   0.01925   0.01213  -0.0539   0.0170   1.0000
   8.500   1.1366   0.02006   0.01301  -0.0511   0.0163   1.0000
   8.750   1.1469   0.02094   0.01396  -0.0484   0.0158   1.0000
   9.000   1.1574   0.02184   0.01493  -0.0459   0.0150   1.0000
   9.250   1.1682   0.02273   0.01585  -0.0435   0.0142   1.0000
   9.500   1.1752   0.02396   0.01714  -0.0407   0.0138   1.0000
   9.750   1.1803   0.02555   0.01877  -0.0379   0.0133   1.0000
  10.000   1.1889   0.02832   0.02157  -0.0357   0.0128   1.0000
  10.250   1.2014   0.02923   0.02260  -0.0338   0.0126   1.0000
  10.500   1.2144   0.03040   0.02387  -0.0321   0.0123   1.0000
  10.750   1.2286   0.03186   0.02546  -0.0306   0.0121   1.0000
  11.000   1.2441   0.03363   0.02735  -0.0293   0.0120   1.0000
  11.250   1.2583   0.03555   0.02943  -0.0279   0.0118   1.0000
  11.500   1.2692   0.03748   0.03152  -0.0263   0.0116   1.0000
  11.750   1.2763   0.03924   0.03344  -0.0244   0.0112   1.0000
  12.000   1.2814   0.04109   0.03544  -0.0225   0.0109   1.0000
  12.250   1.2856   0.04353   0.03807  -0.0207   0.0108   1.0000
  12.500   1.2866   0.04647   0.04124  -0.0188   0.0109   1.0000
  12.750   1.2821   0.05038   0.04542  -0.0168   0.0115   1.0000
  13.000   1.2738   0.05410   0.04938  -0.0151   0.0117   1.0000
  13.250   1.2627   0.05802   0.05351  -0.0137   0.0119   1.0000
  13.500   1.2489   0.06233   0.05803  -0.0128   0.0121   1.0000
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