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GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 620 AIRFOIL (goe620-il)
Reynolds number: 100,000
Max Cl/Cd: 43.12 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe620-il-100000-n5.txt
Download as CSV file: xf-goe620-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 620 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0731   0.09914   0.09338  -0.1063   0.9272   0.0630
 -10.750  -0.0671   0.09384   0.08805  -0.1110   0.9235   0.0635
 -10.500  -0.0664   0.08733   0.08151  -0.1168   0.9199   0.0644
 -10.000  -0.2607   0.04902   0.04263  -0.1459   0.8882   0.0632
  -9.750  -0.2954   0.04535   0.03862  -0.1441   0.8751   0.0632
  -9.500  -0.2998   0.04182   0.03469  -0.1448   0.8689   0.0637
  -9.250  -0.3091   0.04003   0.03262  -0.1415   0.8591   0.0641
  -9.000  -0.3024   0.03773   0.02993  -0.1407   0.8534   0.0650
  -8.750  -0.2842   0.03569   0.02753  -0.1412   0.8501   0.0661
  -8.500  -0.2798   0.03512   0.02696  -0.1378   0.8415   0.0669
  -8.250  -0.2601   0.03409   0.02584  -0.1373   0.8368   0.0680
  -8.000  -0.2350   0.03284   0.02443  -0.1377   0.8335   0.0693
  -7.750  -0.2144   0.03170   0.02309  -0.1371   0.8292   0.0705
  -7.500  -0.2073   0.03102   0.02226  -0.1340   0.8213   0.0715
  -7.250  -0.1832   0.02990   0.02089  -0.1338   0.8172   0.0728
  -7.000  -0.1537   0.02892   0.01987  -0.1345   0.8144   0.0746
  -6.750  -0.1392   0.02850   0.01943  -0.1324   0.8082   0.0761
  -6.500  -0.1228   0.02801   0.01887  -0.1306   0.8022   0.0779
  -6.250  -0.0956   0.02722   0.01794  -0.1306   0.7985   0.0802
  -6.000  -0.0645   0.02638   0.01699  -0.1313   0.7957   0.0824
  -5.750  -0.0521   0.02612   0.01675  -0.1288   0.7893   0.0841
  -5.500  -0.0339   0.02575   0.01634  -0.1271   0.7834   0.0868
  -5.250  -0.0051   0.02516   0.01561  -0.1273   0.7798   0.0908
  -5.000   0.0266   0.02451   0.01497  -0.1280   0.7770   0.0948
  -4.750   0.0373   0.02439   0.01482  -0.1250   0.7700   0.0984
  -4.500   0.0571   0.02404   0.01445  -0.1236   0.7644   0.1033
  -4.250   0.0866   0.02352   0.01389  -0.1239   0.7608   0.1116
  -4.000   0.1200   0.02289   0.01328  -0.1248   0.7580   0.1235
  -3.750   0.1270   0.02292   0.01337  -0.1212   0.7501   0.1330
  -3.500   0.1502   0.02263   0.01313  -0.1203   0.7449   0.1500
  -3.250   0.1821   0.02225   0.01277  -0.1209   0.7414   0.1731
  -3.000   0.2188   0.02187   0.01237  -0.1224   0.7387   0.1970
  -2.750   0.2214   0.02217   0.01272  -0.1179   0.7296   0.2089
  -2.500   0.2487   0.02201   0.01254  -0.1177   0.7249   0.2279
  -2.250   0.2832   0.02173   0.01225  -0.1187   0.7216   0.2495
  -2.000   0.3034   0.02176   0.01230  -0.1172   0.7157   0.2686
  -1.750   0.3176   0.02189   0.01246  -0.1147   0.7085   0.2857
  -1.500   0.3488   0.02169   0.01227  -0.1151   0.7043   0.3075
  -1.250   0.3865   0.02139   0.01194  -0.1166   0.7012   0.3287
  -1.000   0.3884   0.02177   0.01235  -0.1120   0.6920   0.3401
  -0.750   0.4159   0.02164   0.01221  -0.1117   0.6869   0.3576
  -0.500   0.4526   0.02134   0.01190  -0.1130   0.6834   0.3784
  -0.250   0.4601   0.02160   0.01224  -0.1094   0.6751   0.3928
   0.000   0.4830   0.02154   0.01223  -0.1083   0.6692   0.4132
   0.500   0.5290   0.02148   0.01224  -0.1063   0.6576   0.4583
   0.750   0.5498   0.02147   0.01230  -0.1049   0.6511   0.4823
   1.000   0.5878   0.02118   0.01205  -0.1064   0.6472   0.5163
   1.250   0.5945   0.02145   0.01242  -0.1026   0.6390   0.5432
   1.500   0.6174   0.02139   0.01245  -0.1016   0.6327   0.5822
   1.750   0.6562   0.02098   0.01215  -0.1031   0.6287   0.6381
   2.000   0.6598   0.02127   0.01269  -0.0988   0.6199   0.6954
   2.500   0.7843   0.02062   0.01228  -0.1117   0.6093   1.0000
   2.750   0.7834   0.02111   0.01272  -0.1066   0.5994   1.0000
   3.000   0.8199   0.02084   0.01227  -0.1078   0.5930   1.0000
   3.250   0.8208   0.02134   0.01275  -0.1031   0.5827   1.0000
   3.500   0.8543   0.02114   0.01238  -0.1038   0.5758   1.0000
   3.750   0.8598   0.02165   0.01287  -0.1000   0.5663   1.0000
   4.000   0.8878   0.02165   0.01275  -0.0999   0.5596   1.0000
   4.250   0.9018   0.02204   0.01310  -0.0976   0.5517   1.0000
   4.500   0.9222   0.02228   0.01326  -0.0963   0.5443   1.0000
   4.750   0.9483   0.02239   0.01328  -0.0960   0.5379   1.0000
   5.000   0.9591   0.02292   0.01380  -0.0933   0.5296   1.0000
   5.250   0.9888   0.02293   0.01369  -0.0935   0.5232   1.0000
   5.500   0.9972   0.02356   0.01433  -0.0906   0.5144   1.0000
   5.750   1.0203   0.02374   0.01442  -0.0898   0.5066   1.0000
   6.000   1.0334   0.02427   0.01493  -0.0877   0.4982   1.0000
   6.250   1.0509   0.02464   0.01525  -0.0861   0.4899   1.0000
   6.500   1.0665   0.02511   0.01568  -0.0844   0.4814   1.0000
   6.750   1.0800   0.02564   0.01619  -0.0825   0.4724   1.0000
   7.000   1.0972   0.02609   0.01659  -0.0810   0.4646   1.0000
   7.250   1.1075   0.02680   0.01731  -0.0788   0.4556   1.0000
   7.500   1.1275   0.02716   0.01760  -0.0778   0.4482   1.0000
   7.750   1.1344   0.02808   0.01858  -0.0753   0.4395   1.0000
   8.000   1.1562   0.02837   0.01878  -0.0745   0.4326   1.0000
   8.250   1.1609   0.02947   0.01996  -0.0720   0.4237   1.0000
   8.500   1.1780   0.02999   0.02043  -0.0707   0.4164   1.0000
   8.750   1.1862   0.03098   0.02146  -0.0687   0.4081   1.0000
   9.000   1.1991   0.03175   0.02221  -0.0672   0.4004   1.0000
   9.250   1.2110   0.03261   0.02308  -0.0656   0.3928   1.0000
   9.500   1.2198   0.03366   0.02416  -0.0638   0.3849   1.0000
   9.750   1.2372   0.03423   0.02467  -0.0628   0.3787   1.0000
  10.000   1.2419   0.03563   0.02617  -0.0609   0.3710   1.0000
  10.250   1.2562   0.03640   0.02692  -0.0597   0.3645   1.0000
  10.500   1.2641   0.03764   0.02821  -0.0581   0.3574   1.0000
  10.750   1.2725   0.03885   0.02945  -0.0566   0.3503   1.0000
  11.000   1.2849   0.03978   0.03035  -0.0554   0.3436   1.0000
  11.250   1.2877   0.04147   0.03213  -0.0538   0.3359   1.0000
  11.500   1.3013   0.04233   0.03295  -0.0527   0.3298   1.0000
  11.750   1.3049   0.04408   0.03479  -0.0512   0.3231   1.0000
  12.000   1.3125   0.04551   0.03626  -0.0500   0.3172   1.0000
  12.250   1.3270   0.04634   0.03706  -0.0491   0.3119   1.0000
  12.500   1.3260   0.04861   0.03946  -0.0477   0.3051   1.0000
  12.750   1.3336   0.05009   0.04097  -0.0467   0.2990   1.0000
  13.000   1.3432   0.05142   0.04231  -0.0457   0.2937   1.0000
  13.250   1.3430   0.05378   0.04479  -0.0446   0.2878   1.0000
  13.500   1.3507   0.05533   0.04639  -0.0437   0.2824   1.0000
  13.750   1.3605   0.05672   0.04778  -0.0429   0.2774   1.0000
  14.000   1.3567   0.05958   0.05080  -0.0420   0.2714   1.0000
  14.250   1.3620   0.06146   0.05272  -0.0413   0.2659   1.0000
  14.500   1.3720   0.06284   0.05410  -0.0406   0.2608   1.0000
  14.750   1.3638   0.06637   0.05782  -0.0400   0.2545   1.0000
  15.000   1.3672   0.06855   0.06004  -0.0394   0.2487   1.0000
  15.250   1.3729   0.07049   0.06200  -0.0389   0.2430   1.0000
  15.500   1.3621   0.07455   0.06622  -0.0387   0.2361   1.0000
  15.750   1.3690   0.07634   0.06800  -0.0383   0.2301   1.0000
  16.000   1.3606   0.08023   0.07202  -0.0382   0.2234   1.0000
  16.250   1.3553   0.08376   0.07564  -0.0382   0.2166   1.0000
  16.500   1.3648   0.08526   0.07711  -0.0379   0.2112   1.0000
  16.750   1.3473   0.09066   0.08270  -0.0385   0.2040   1.0000
  17.000   1.3518   0.09291   0.08497  -0.0385   0.1986   1.0000
  17.250   1.3481   0.09644   0.08858  -0.0389   0.1933   1.0000
  17.500   1.3370   0.10113   0.09339  -0.0397   0.1875   1.0000
  17.750   1.3452   0.10288   0.09515  -0.0397   0.1833   1.0000
  18.000   1.3337   0.10772   0.10010  -0.0407   0.1783   1.0000
  18.250   1.3228   0.11254   0.10504  -0.0419   0.1734   1.0000
  18.500   1.3319   0.11417   0.10666  -0.0421   0.1698   1.0000
  18.750   1.3208   0.11913   0.11172  -0.0435   0.1657   1.0000
  19.000   1.3039   0.12511   0.11784  -0.0456   0.1613   1.0000
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