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GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 685 AIRFOIL (goe685-il)
Reynolds number: 100,000
Max Cl/Cd: 52.47 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe685-il-100000.txt
Download as CSV file: xf-goe685-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 685 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3261   0.09571   0.09078  -0.0316   1.0000   0.1639
  -8.000  -0.6163   0.04632   0.04081  -0.0626   1.0000   0.0937
  -7.750  -0.6204   0.04044   0.03434  -0.0640   1.0000   0.0939
  -7.500  -0.6106   0.03786   0.03163  -0.0634   1.0000   0.0951
  -7.250  -0.5966   0.03691   0.03071  -0.0622   1.0000   0.0973
  -7.000  -0.5828   0.03512   0.02871  -0.0617   1.0000   0.0997
  -6.750  -0.5683   0.03261   0.02576  -0.0617   1.0000   0.1024
  -6.500  -0.5391   0.02986   0.02234  -0.0640   0.9965   0.1059
  -6.250  -0.5003   0.02907   0.02167  -0.0668   0.9898   0.1108
  -6.000  -0.4600   0.02773   0.01995  -0.0700   0.9831   0.1193
  -5.750  -0.4220   0.02721   0.01940  -0.0725   0.9747   0.1293
  -5.500  -0.3781   0.02650   0.01853  -0.0758   0.9671   0.1458
  -5.250  -0.3385   0.02670   0.01901  -0.0781   0.9568   0.1651
  -5.000  -0.3000   0.02703   0.01931  -0.0801   0.9465   0.1885
  -4.750  -0.2541   0.02767   0.02001  -0.0832   0.9386   0.2083
  -4.500  -0.2231   0.02807   0.02036  -0.0837   0.9278   0.2230
  -4.250  -0.1764   0.02875   0.02109  -0.0868   0.9215   0.2394
  -4.000  -0.1488   0.02962   0.02220  -0.0862   0.9101   0.2504
  -3.750  -0.1024   0.02981   0.02240  -0.0892   0.9046   0.2650
  -3.500  -0.0765   0.02921   0.02159  -0.0892   0.8933   0.2753
  -3.250  -0.0293   0.02870   0.02099  -0.0925   0.8880   0.2866
  -3.000  -0.0022   0.02817   0.02038  -0.0925   0.8770   0.2940
  -2.750   0.0453   0.02739   0.01942  -0.0959   0.8717   0.3046
  -2.500   0.0763   0.02679   0.01876  -0.0964   0.8617   0.3117
  -2.250   0.1192   0.02600   0.01784  -0.0988   0.8552   0.3209
  -2.000   0.1521   0.02532   0.01704  -0.0995   0.8457   0.3283
  -1.750   0.1914   0.02461   0.01626  -0.1010   0.8381   0.3377
  -1.500   0.2227   0.02398   0.01553  -0.1013   0.8279   0.3453
  -1.250   0.2619   0.02323   0.01471  -0.1026   0.8203   0.3549
  -1.000   0.2904   0.02273   0.01417  -0.1023   0.8085   0.3638
  -0.750   0.3314   0.02197   0.01325  -0.1038   0.8016   0.3759
  -0.500   0.3576   0.02150   0.01285  -0.1031   0.7884   0.3841
  -0.250   0.3881   0.02105   0.01232  -0.1030   0.7768   0.3951
   0.000   0.4245   0.02043   0.01164  -0.1037   0.7678   0.4081
   0.250   0.4512   0.02008   0.01133  -0.1030   0.7538   0.4188
   0.500   0.4796   0.01979   0.01100  -0.1026   0.7405   0.4305
   0.750   0.5099   0.01952   0.01066  -0.1025   0.7284   0.4440
   1.000   0.5409   0.01919   0.01034  -0.1024   0.7168   0.4577
   1.250   0.5666   0.01909   0.01029  -0.1017   0.7026   0.4713
   1.500   0.5931   0.01900   0.01023  -0.1011   0.6892   0.4868
   1.750   0.6217   0.01886   0.01011  -0.1008   0.6774   0.5047
   2.000   0.6504   0.01875   0.01004  -0.1005   0.6655   0.5268
   2.250   0.6756   0.01873   0.01016  -0.0998   0.6525   0.5535
   2.500   0.7021   0.01852   0.01018  -0.0992   0.6413   0.6019
   2.750   0.7495   0.01762   0.01000  -0.1021   0.6298   1.0000
   3.000   0.7737   0.01799   0.01025  -0.1014   0.6180   1.0000
   3.250   0.8016   0.01828   0.01037  -0.1012   0.6093   1.0000
   3.500   0.8262   0.01863   0.01066  -0.1005   0.5995   1.0000
   3.750   0.8521   0.01897   0.01091  -0.0999   0.5907   1.0000
   4.000   0.8776   0.01926   0.01115  -0.0993   0.5815   1.0000
   4.250   0.9022   0.01964   0.01150  -0.0986   0.5728   1.0000
   4.500   0.9280   0.01994   0.01174  -0.0980   0.5642   1.0000
   4.750   0.9521   0.02035   0.01215  -0.0972   0.5557   1.0000
   5.000   0.9778   0.02065   0.01242  -0.0966   0.5473   1.0000
   5.250   1.0013   0.02105   0.01283  -0.0957   0.5384   1.0000
   5.500   1.0273   0.02133   0.01308  -0.0951   0.5300   1.0000
   5.750   1.0504   0.02181   0.01362  -0.0942   0.5220   1.0000
   6.000   1.0754   0.02217   0.01398  -0.0935   0.5138   1.0000
   6.250   1.0988   0.02261   0.01447  -0.0926   0.5053   1.0000
   6.500   1.1239   0.02290   0.01476  -0.0919   0.4963   1.0000
   6.750   1.1454   0.02334   0.01527  -0.0907   0.4865   1.0000
   7.000   1.1743   0.02348   0.01532  -0.0904   0.4770   1.0000
   7.250   1.1917   0.02394   0.01592  -0.0886   0.4656   1.0000
   7.500   1.2146   0.02419   0.01618  -0.0875   0.4542   1.0000
   7.750   1.2398   0.02426   0.01616  -0.0866   0.4415   1.0000
   8.000   1.2591   0.02442   0.01637  -0.0848   0.4276   1.0000
   8.250   1.2758   0.02469   0.01673  -0.0828   0.4138   1.0000
   8.500   1.2938   0.02498   0.01707  -0.0809   0.4009   1.0000
   8.750   1.3130   0.02520   0.01733  -0.0793   0.3882   1.0000
   9.000   1.3306   0.02536   0.01749  -0.0773   0.3744   1.0000
   9.250   1.3423   0.02561   0.01784  -0.0745   0.3597   1.0000
   9.500   1.3521   0.02592   0.01828  -0.0715   0.3448   1.0000
   9.750   1.3603   0.02627   0.01876  -0.0683   0.3294   1.0000
  10.000   1.3652   0.02666   0.01922  -0.0646   0.3125   1.0000
  10.250   1.3641   0.02719   0.01977  -0.0601   0.2931   1.0000
  10.500   1.3601   0.02803   0.02065  -0.0557   0.2685   1.0000
  10.750   1.3526   0.02933   0.02184  -0.0514   0.2388   1.0000
  11.000   1.3396   0.03132   0.02361  -0.0472   0.2075   1.0000
  11.250   1.3237   0.03397   0.02602  -0.0436   0.1814   1.0000
  11.500   1.3073   0.03705   0.02892  -0.0406   0.1608   1.0000
  11.750   1.2947   0.04021   0.03199  -0.0383   0.1429   1.0000
  12.000   1.2873   0.04317   0.03495  -0.0368   0.1277   1.0000
  12.250   1.2812   0.04617   0.03792  -0.0357   0.1178   1.0000
  12.500   1.2794   0.04891   0.04068  -0.0347   0.1100   1.0000
  12.750   1.2756   0.05187   0.04355  -0.0339   0.1047   1.0000
  13.000   1.2764   0.05446   0.04617  -0.0331   0.0996   1.0000
  13.250   1.2779   0.05692   0.04851  -0.0323   0.0955   1.0000
  13.500   1.2871   0.05870   0.05028  -0.0311   0.0915   1.0000
  13.750   1.2992   0.06024   0.05180  -0.0299   0.0878   1.0000
  14.000   1.3294   0.06043   0.05172  -0.0278   0.0832   1.0000
  14.250   1.3411   0.06242   0.05389  -0.0270   0.0807   1.0000
  14.500   1.3591   0.06409   0.05565  -0.0260   0.0780   1.0000
  14.750   1.4186   0.06459   0.05586  -0.0249   0.0731   1.0000
  15.000   1.4142   0.06763   0.05920  -0.0242   0.0721   1.0000
  15.250   1.4130   0.07082   0.06266  -0.0237   0.0711   1.0000
  15.500   1.4110   0.07427   0.06638  -0.0234   0.0701   1.0000
  15.750   1.4066   0.07801   0.07038  -0.0233   0.0692   1.0000
  16.000   1.3997   0.08203   0.07464  -0.0235   0.0683   1.0000
  16.250   1.3914   0.08630   0.07913  -0.0240   0.0675   1.0000
  16.500   1.3824   0.09078   0.08381  -0.0248   0.0668   1.0000
  16.750   1.3728   0.09547   0.08871  -0.0259   0.0661   1.0000
  17.000   1.3627   0.10039   0.09382  -0.0272   0.0655   1.0000
  17.250   1.3099   0.11059   0.10448  -0.0328   0.0668   1.0000
  17.500   1.2514   0.12385   0.11817  -0.0411   0.0688   1.0000
  17.750   1.1949   0.13901   0.13363  -0.0509   0.0709   1.0000
  18.000   1.1480   0.15440   0.14917  -0.0606   0.0727   1.0000
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