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GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 286 AIRFOIL (goe286-il)
Reynolds number: 50,000
Max Cl/Cd: 37.61 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe286-il-50000-n5.txt
Download as CSV file: xf-goe286-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 286 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3584   0.09720   0.09067  -0.0197   1.0000   0.1218
  -7.500  -0.3625   0.09501   0.08858  -0.0235   1.0000   0.1263
  -7.250  -0.3688   0.09330   0.08691  -0.0326   1.0000   0.1282
  -7.000  -0.3544   0.08816   0.08187  -0.0271   1.0000   0.1305
  -6.750  -0.3454   0.08509   0.07885  -0.0257   1.0000   0.1359
  -6.500  -0.3501   0.08359   0.07732  -0.0345   1.0000   0.1437
  -6.250  -0.3404   0.07930   0.07317  -0.0289   1.0000   0.1473
  -6.000  -0.3347   0.07662   0.07054  -0.0282   1.0000   0.1529
  -5.750  -0.3327   0.07394   0.06785  -0.0322   1.0000   0.1610
  -5.500  -0.3263   0.07095   0.06493  -0.0300   1.0000   0.1637
  -5.000  -0.2850   0.05845   0.05163  -0.0418   1.0000   0.0812
  -4.750  -0.2734   0.05556   0.04865  -0.0418   1.0000   0.0806
  -4.500  -0.2599   0.05274   0.04567  -0.0421   1.0000   0.0805
  -4.250  -0.2245   0.04888   0.04154  -0.0465   0.9926   0.0793
  -4.000  -0.1829   0.04493   0.03724  -0.0517   0.9835   0.0769
  -3.750  -0.1386   0.04121   0.03303  -0.0568   0.9738   0.0750
  -3.500  -0.0937   0.03799   0.02929  -0.0613   0.9626   0.0743
  -3.250  -0.0491   0.03552   0.02635  -0.0653   0.9503   0.0767
  -3.000  -0.0051   0.03321   0.02355  -0.0687   0.9373   0.0779
  -2.750   0.0364   0.03116   0.02107  -0.0714   0.9237   0.0780
  -2.500   0.0751   0.02946   0.01899  -0.0732   0.9092   0.0785
  -2.250   0.1120   0.02801   0.01718  -0.0745   0.8944   0.0795
  -2.000   0.1479   0.02680   0.01564  -0.0754   0.8795   0.0813
  -1.750   0.1820   0.02570   0.01445  -0.0761   0.8643   0.0853
  -1.500   0.2148   0.02485   0.01346  -0.0764   0.8489   0.0900
  -1.250   0.2478   0.02405   0.01245  -0.0764   0.8333   0.0939
  -1.000   0.2790   0.02334   0.01157  -0.0762   0.8173   0.0982
  -0.750   0.3082   0.02272   0.01088  -0.0758   0.8007   0.1051
  -0.500   0.3365   0.02220   0.01029  -0.0752   0.7837   0.1172
  -0.250   0.3641   0.02163   0.00978  -0.0747   0.7664   0.1481
   0.000   0.3950   0.01865   0.00928  -0.0745   0.7497   1.0000
   0.250   0.4215   0.01878   0.00895  -0.0736   0.7316   1.0000
   0.500   0.4473   0.01893   0.00878  -0.0727   0.7128   1.0000
   0.750   0.4734   0.01908   0.00865  -0.0718   0.6952   1.0000
   1.000   0.4995   0.01925   0.00855  -0.0710   0.6781   1.0000
   1.250   0.5256   0.01945   0.00851  -0.0702   0.6614   1.0000
   1.500   0.5516   0.01970   0.00853  -0.0694   0.6453   1.0000
   1.750   0.5776   0.01999   0.00861  -0.0687   0.6295   1.0000
   2.000   0.6038   0.02031   0.00875  -0.0681   0.6133   1.0000
   2.250   0.6297   0.02066   0.00895  -0.0675   0.5971   1.0000
   2.500   0.6555   0.02103   0.00918  -0.0670   0.5811   1.0000
   2.750   0.6811   0.02139   0.00944  -0.0664   0.5654   1.0000
   3.000   0.7066   0.02176   0.00974  -0.0659   0.5502   1.0000
   3.250   0.7320   0.02213   0.01005  -0.0654   0.5357   1.0000
   3.500   0.7573   0.02250   0.01037  -0.0650   0.5222   1.0000
   3.750   0.7827   0.02288   0.01071  -0.0645   0.5098   1.0000
   4.000   0.8083   0.02323   0.01100  -0.0640   0.4985   1.0000
   4.250   0.8335   0.02363   0.01140  -0.0635   0.4870   1.0000
   4.500   0.8585   0.02406   0.01186  -0.0631   0.4758   1.0000
   4.750   0.8837   0.02447   0.01224  -0.0626   0.4658   1.0000
   5.000   0.9087   0.02489   0.01266  -0.0621   0.4556   1.0000
   5.250   0.9332   0.02540   0.01325  -0.0616   0.4455   1.0000
   5.500   0.9588   0.02584   0.01365  -0.0611   0.4379   1.0000
   5.750   0.9828   0.02648   0.01445  -0.0608   0.4289   1.0000
   6.000   1.0080   0.02697   0.01496  -0.0603   0.4211   1.0000
   6.250   1.0313   0.02762   0.01576  -0.0598   0.4115   1.0000
   6.500   1.0554   0.02819   0.01640  -0.0592   0.4030   1.0000
   6.750   1.0786   0.02879   0.01712  -0.0586   0.3933   1.0000
   7.000   1.1004   0.02941   0.01790  -0.0579   0.3820   1.0000
   7.250   1.1222   0.02994   0.01852  -0.0570   0.3701   1.0000
   7.500   1.1442   0.03042   0.01904  -0.0561   0.3586   1.0000
   7.750   1.1636   0.03114   0.01997  -0.0551   0.3462   1.0000
   8.000   1.1829   0.03185   0.02090  -0.0541   0.3344   1.0000
   8.250   1.2026   0.03253   0.02173  -0.0531   0.3234   1.0000
   8.500   1.2221   0.03318   0.02251  -0.0520   0.3125   1.0000
   8.750   1.2386   0.03411   0.02370  -0.0508   0.3005   1.0000
   9.000   1.2550   0.03504   0.02488  -0.0496   0.2889   1.0000
   9.250   1.2705   0.03593   0.02595  -0.0482   0.2770   1.0000
   9.500   1.2847   0.03682   0.02697  -0.0466   0.2648   1.0000
   9.750   1.2961   0.03795   0.02831  -0.0450   0.2518   1.0000
  10.000   1.3060   0.03926   0.02983  -0.0433   0.2396   1.0000
  10.250   1.3154   0.04059   0.03135  -0.0416   0.2292   1.0000
  10.500   1.3237   0.04185   0.03272  -0.0397   0.2198   1.0000
  10.750   1.3259   0.04364   0.03472  -0.0375   0.2103   1.0000
  11.000   1.3280   0.04534   0.03652  -0.0355   0.2015   1.0000
  11.250   1.3267   0.04739   0.03868  -0.0338   0.1918   1.0000
  11.500   1.3230   0.04997   0.04141  -0.0325   0.1822   1.0000
  11.750   1.3194   0.05262   0.04412  -0.0317   0.1735   1.0000
  12.000   1.3141   0.05563   0.04718  -0.0312   0.1645   1.0000
  12.250   1.3060   0.05933   0.05100  -0.0313   0.1557   1.0000
  12.500   1.2984   0.06302   0.05471  -0.0315   0.1474   1.0000
  12.750   1.2904   0.06690   0.05859  -0.0320   0.1391   1.0000
  13.000   1.2807   0.07134   0.06312  -0.0328   0.1315   1.0000
  13.250   1.2746   0.07500   0.06667  -0.0331   0.1235   1.0000
  13.500   1.2616   0.08038   0.07229  -0.0347   0.1168   1.0000
  13.750   1.2543   0.08443   0.07629  -0.0354   0.1092   1.0000
  14.000   1.2391   0.09057   0.08273  -0.0376   0.1031   1.0000
  14.250   1.2289   0.09560   0.08784  -0.0393   0.0961   1.0000
  14.500   1.2117   0.10271   0.09527  -0.0423   0.0905   1.0000
  14.750   1.1996   0.10877   0.10147  -0.0448   0.0847   1.0000
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