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GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 365 AIRFOIL (goe365-il)
Reynolds number: 100,000
Max Cl/Cd: 55.84 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe365-il-100000.txt
Download as CSV file: xf-goe365-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 365 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3310   0.11154   0.10728  -0.0289   1.0000   0.0698
  -8.500  -0.3528   0.11153   0.10737  -0.0263   1.0000   0.0701
  -8.250  -0.3772   0.11155   0.10748  -0.0243   1.0000   0.0703
  -8.000  -0.3879   0.11009   0.10608  -0.0292   0.9950   0.0707
  -7.750  -0.3791   0.10488   0.10086  -0.0375   0.9876   0.0714
  -7.500  -0.3450   0.09933   0.09531  -0.0299   0.9887   0.0745
  -7.250  -0.3298   0.09585   0.09182  -0.0334   0.9837   0.0775
  -7.000  -0.3235   0.09261   0.08859  -0.0376   0.9757   0.0805
  -6.750  -0.3159   0.08902   0.08489  -0.0498   0.9645   0.0844
  -6.500  -0.3004   0.08347   0.07929  -0.0557   0.9592   0.0866
  -6.250  -0.2896   0.08080   0.07669  -0.0520   0.9540   0.0896
  -6.000  -0.2728   0.07756   0.07341  -0.0549   0.9477   0.0953
  -5.750  -0.2637   0.07410   0.06957  -0.0641   0.9376   0.1014
  -5.500  -0.2455   0.07009   0.06574  -0.0624   0.9337   0.1044
  -5.250  -0.2181   0.06687   0.06242  -0.0661   0.9293   0.1125
  -5.000  -0.2121   0.06383   0.05916  -0.0678   0.9199   0.1189
  -4.750  -0.1788   0.06153   0.05646  -0.0731   0.9149   0.1335
  -4.500  -0.1754   0.05826   0.05344  -0.0697   0.9073   0.1365
  -4.250  -0.1490   0.05542   0.05046  -0.0721   0.9017   0.1526
  -4.000  -0.1307   0.05334   0.04824  -0.0727   0.8947   0.1682
  -3.750  -0.1104   0.05101   0.04586  -0.0730   0.8878   0.1853
  -3.500  -0.0760   0.04854   0.04325  -0.0758   0.8837   0.2173
  -3.250  -0.0713   0.04710   0.04186  -0.0727   0.8741   0.2351
  -1.750   0.1488   0.03390   0.02581  -0.0808   0.8379   0.1307
  -1.250   0.2135   0.03117   0.02249  -0.0806   0.8239   0.1092
  -1.000   0.2674   0.02976   0.02064  -0.0836   0.8210   0.1021
  -0.750   0.2821   0.02960   0.02038  -0.0811   0.8099   0.1017
  -0.500   0.3335   0.02800   0.01878  -0.0845   0.8066   0.1041
  -0.250   0.3554   0.02767   0.01844  -0.0831   0.7969   0.1042
   0.000   0.3996   0.02655   0.01736  -0.0850   0.7920   0.1057
   0.250   0.4388   0.02567   0.01651  -0.0861   0.7867   0.1091
   0.500   0.4633   0.02540   0.01621  -0.0850   0.7768   0.1144
   0.750   0.5128   0.02429   0.01506  -0.0877   0.7734   0.1297
   1.000   0.6015   0.02156   0.01457  -0.0990   0.7656   1.0000
   1.250   0.6435   0.02105   0.01374  -0.1004   0.7590   1.0000
   1.500   0.6667   0.02097   0.01351  -0.0988   0.7465   1.0000
   1.750   0.6985   0.02054   0.01291  -0.0984   0.7349   1.0000
   2.000   0.7418   0.01972   0.01189  -0.0997   0.7256   1.0000
   2.250   0.7625   0.01969   0.01178  -0.0978   0.7118   1.0000
   2.500   0.7844   0.01971   0.01172  -0.0962   0.6990   1.0000
   2.750   0.8105   0.01961   0.01153  -0.0953   0.6875   1.0000
   3.000   0.8440   0.01929   0.01109  -0.0955   0.6776   1.0000
   3.250   0.8637   0.01935   0.01112  -0.0936   0.6638   1.0000
   3.500   0.8851   0.01936   0.01109  -0.0920   0.6504   1.0000
   3.750   0.9079   0.01932   0.01101  -0.0906   0.6370   1.0000
   4.000   0.9317   0.01925   0.01090  -0.0893   0.6237   1.0000
   4.250   0.9556   0.01915   0.01075  -0.0881   0.6097   1.0000
   4.500   0.9789   0.01907   0.01062  -0.0868   0.5947   1.0000
   4.750   1.0015   0.01903   0.01054  -0.0854   0.5787   1.0000
   5.000   1.0239   0.01903   0.01047  -0.0840   0.5616   1.0000
   5.250   1.0464   0.01908   0.01042  -0.0826   0.5436   1.0000
   5.500   1.0695   0.01921   0.01042  -0.0814   0.5252   1.0000
   5.750   1.0895   0.01951   0.01063  -0.0797   0.5053   1.0000
   6.000   1.1082   0.01990   0.01093  -0.0779   0.4843   1.0000
   6.250   1.1285   0.02033   0.01120  -0.0764   0.4638   1.0000
   6.500   1.1466   0.02087   0.01164  -0.0746   0.4431   1.0000
   6.750   1.1634   0.02147   0.01214  -0.0727   0.4229   1.0000
   7.000   1.1813   0.02209   0.01265  -0.0710   0.4046   1.0000
   7.250   1.1991   0.02272   0.01319  -0.0694   0.3880   1.0000
   7.500   1.2172   0.02340   0.01382  -0.0678   0.3735   1.0000
   7.750   1.2359   0.02410   0.01449  -0.0665   0.3607   1.0000
   8.000   1.2572   0.02483   0.01516  -0.0656   0.3500   1.0000
   8.250   1.2779   0.02554   0.01584  -0.0646   0.3400   1.0000
   8.500   1.2954   0.02631   0.01670  -0.0631   0.3306   1.0000
   8.750   1.3196   0.02702   0.01731  -0.0628   0.3221   1.0000
   9.000   1.3329   0.02776   0.01821  -0.0607   0.3135   1.0000
   9.250   1.3581   0.02856   0.01894  -0.0606   0.3064   1.0000
   9.500   1.3719   0.02940   0.02000  -0.0587   0.2995   1.0000
   9.750   1.3994   0.03021   0.02072  -0.0590   0.2931   1.0000
  10.000   1.4117   0.03119   0.02194  -0.0569   0.2873   1.0000
  10.250   1.4312   0.03207   0.02293  -0.0560   0.2813   1.0000
  10.500   1.4551   0.03308   0.02397  -0.0558   0.2756   1.0000
  10.750   1.4627   0.03405   0.02518  -0.0531   0.2695   1.0000
  11.000   1.4864   0.03474   0.02576  -0.0528   0.2615   1.0000
  11.250   1.4845   0.03561   0.02690  -0.0487   0.2547   1.0000
  11.500   1.5012   0.03614   0.02736  -0.0473   0.2460   1.0000
  11.750   1.4947   0.03702   0.02847  -0.0426   0.2397   1.0000
  12.000   1.5127   0.03760   0.02895  -0.0416   0.2317   1.0000
  12.250   1.5042   0.03875   0.03038  -0.0370   0.2263   1.0000
  12.500   1.5196   0.03937   0.03095  -0.0358   0.2193   1.0000
  12.750   1.5148   0.04068   0.03251  -0.0323   0.2139   1.0000
  13.000   1.5132   0.04174   0.03371  -0.0294   0.2077   1.0000
  13.250   1.5210   0.04267   0.03466  -0.0276   0.2015   1.0000
  13.500   1.5112   0.04439   0.03666  -0.0244   0.1965   1.0000
  13.750   1.5175   0.04525   0.03753  -0.0228   0.1903   1.0000
  14.000   1.5069   0.04720   0.03971  -0.0202   0.1850   1.0000
  14.250   1.4978   0.04909   0.04177  -0.0181   0.1790   1.0000
  14.500   1.4954   0.05066   0.04339  -0.0166   0.1730   1.0000
  14.750   1.4812   0.05353   0.04657  -0.0151   0.1678   1.0000
  15.000   1.4749   0.05561   0.04870  -0.0141   0.1613   1.0000
  15.250   1.4574   0.05929   0.05266  -0.0134   0.1551   1.0000
  15.500   1.4455   0.06258   0.05609  -0.0131   0.1483   1.0000
  15.750   1.4281   0.06707   0.06082  -0.0135   0.1410   1.0000
  16.000   1.4120   0.07165   0.06550  -0.0143   0.1329   1.0000
  16.250   1.3922   0.07742   0.07152  -0.0159   0.1239   1.0000
  16.500   1.3723   0.08354   0.07780  -0.0178   0.1150   1.0000
  16.750   1.3524   0.08994   0.08425  -0.0201   0.1073   1.0000
  17.000   1.3290   0.09719   0.09153  -0.0230   0.0995   1.0000
  17.250   1.3077   0.10430   0.09868  -0.0259   0.0937   1.0000
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