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GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 286 AIRFOIL (goe286-il)
Reynolds number: 100,000
Max Cl/Cd: 52.25 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe286-il-100000.txt
Download as CSV file: xf-goe286-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3723   0.09993   0.09517  -0.0163   1.0000   0.0836
  -8.000  -0.3812   0.09847   0.09381  -0.0223   1.0000   0.0856
  -7.750  -0.3838   0.09655   0.09189  -0.0348   1.0000   0.0864
  -7.500  -0.3705   0.09013   0.08557  -0.0258   1.0000   0.0882
  -7.250  -0.3581   0.08684   0.08231  -0.0227   1.0000   0.0914
  -7.000  -0.3514   0.08386   0.07937  -0.0242   1.0000   0.0950
  -6.750  -0.3481   0.08108   0.07662  -0.0300   1.0000   0.0995
  -6.500  -0.3478   0.07813   0.07356  -0.0388   1.0000   0.1019
  -6.250  -0.3419   0.07414   0.06972  -0.0337   1.0000   0.1034
  -6.000  -0.3368   0.07152   0.06717  -0.0309   1.0000   0.1057
  -5.750  -0.3325   0.06910   0.06478  -0.0301   1.0000   0.1092
  -5.250  -0.3207   0.06329   0.05880  -0.0349   1.0000   0.1185
  -5.000  -0.3176   0.06099   0.05661  -0.0318   1.0000   0.1210
  -4.750  -0.3119   0.05906   0.05470  -0.0307   1.0000   0.1266
  -4.500  -0.3013   0.05635   0.05182  -0.0334   1.0000   0.1346
  -4.250  -0.2577   0.05291   0.04809  -0.0408   0.9935   0.1491
  -4.000  -0.2187   0.04894   0.04421  -0.0444   0.9852   0.1573
  -3.750  -0.1679   0.04539   0.04032  -0.0526   0.9754   0.1809
  -3.500  -0.1266   0.04206   0.03699  -0.0567   0.9666   0.1998
  -3.250  -0.0824   0.03927   0.03416  -0.0613   0.9584   0.2333
  -2.500   0.0890   0.02738   0.01992  -0.0777   0.9304   0.1127
  -2.250   0.1292   0.02522   0.01737  -0.0794   0.9174   0.1077
  -2.000   0.1688   0.02388   0.01544  -0.0801   0.9038   0.1009
  -1.750   0.2031   0.02223   0.01360  -0.0806   0.8897   0.0996
  -1.500   0.2351   0.02099   0.01217  -0.0804   0.8749   0.0995
  -1.250   0.2650   0.01999   0.01101  -0.0796   0.8596   0.1003
  -1.000   0.2925   0.01896   0.00994  -0.0786   0.8433   0.1041
  -0.750   0.3184   0.01824   0.00923  -0.0772   0.8260   0.1104
  -0.500   0.3438   0.01763   0.00852  -0.0755   0.8081   0.1159
  -0.250   0.3681   0.01693   0.00786  -0.0739   0.7900   0.1254
   0.000   0.3929   0.01641   0.00733  -0.0724   0.7687   0.1483
   0.250   0.4248   0.01354   0.00658  -0.0719   0.7487   1.0000
   0.500   0.4500   0.01360   0.00631  -0.0706   0.7286   1.0000
   0.750   0.4753   0.01370   0.00616  -0.0695   0.7065   1.0000
   1.000   0.5007   0.01382   0.00602  -0.0685   0.6857   1.0000
   1.250   0.5263   0.01401   0.00594  -0.0675   0.6659   1.0000
   1.500   0.5521   0.01428   0.00600  -0.0667   0.6446   1.0000
   1.750   0.5780   0.01459   0.00609  -0.0660   0.6249   1.0000
   2.000   0.6041   0.01494   0.00623  -0.0654   0.6069   1.0000
   2.250   0.6305   0.01529   0.00643  -0.0649   0.5902   1.0000
   2.500   0.6569   0.01563   0.00665  -0.0645   0.5744   1.0000
   2.750   0.6835   0.01595   0.00687  -0.0642   0.5594   1.0000
   3.000   0.7100   0.01625   0.00711  -0.0639   0.5453   1.0000
   3.250   0.7366   0.01654   0.00734  -0.0636   0.5322   1.0000
   3.500   0.7632   0.01683   0.00756  -0.0633   0.5200   1.0000
   3.750   0.7898   0.01710   0.00773  -0.0629   0.5090   1.0000
   4.000   0.8164   0.01738   0.00799  -0.0626   0.4976   1.0000
   4.250   0.8428   0.01771   0.00832  -0.0624   0.4870   1.0000
   4.500   0.8694   0.01804   0.00859  -0.0621   0.4778   1.0000
   4.750   0.8958   0.01838   0.00894  -0.0618   0.4681   1.0000
   5.000   0.9219   0.01875   0.00932  -0.0615   0.4579   1.0000
   5.250   0.9480   0.01908   0.00958  -0.0612   0.4479   1.0000
   5.500   0.9736   0.01938   0.00988  -0.0607   0.4362   1.0000
   5.750   0.9986   0.01971   0.01024  -0.0603   0.4238   1.0000
   6.000   1.0240   0.02010   0.01066  -0.0599   0.4133   1.0000
   6.250   1.0499   0.02050   0.01101  -0.0596   0.4044   1.0000
   6.500   1.0745   0.02090   0.01157  -0.0591   0.3936   1.0000
   6.750   1.0999   0.02134   0.01204  -0.0588   0.3848   1.0000
   7.000   1.1248   0.02176   0.01254  -0.0583   0.3753   1.0000
   7.250   1.1490   0.02221   0.01315  -0.0579   0.3652   1.0000
   7.500   1.1737   0.02262   0.01359  -0.0574   0.3553   1.0000
   7.750   1.1973   0.02301   0.01409  -0.0567   0.3437   1.0000
   8.000   1.2198   0.02339   0.01462  -0.0560   0.3303   1.0000
   8.250   1.2418   0.02377   0.01513  -0.0551   0.3160   1.0000
   8.500   1.2633   0.02418   0.01566  -0.0542   0.3010   1.0000
   8.750   1.2839   0.02465   0.01621  -0.0532   0.2851   1.0000
   9.000   1.3038   0.02518   0.01682  -0.0521   0.2692   1.0000
   9.250   1.3228   0.02577   0.01750  -0.0509   0.2536   1.0000
   9.500   1.3408   0.02641   0.01819  -0.0496   0.2383   1.0000
   9.750   1.3570   0.02707   0.01891  -0.0482   0.2216   1.0000
  10.000   1.3721   0.02784   0.01977  -0.0467   0.2050   1.0000
  10.250   1.3860   0.02876   0.02076  -0.0451   0.1904   1.0000
  10.500   1.3974   0.02984   0.02191  -0.0433   0.1760   1.0000
  10.750   1.4049   0.03113   0.02322  -0.0412   0.1613   1.0000
  11.000   1.4078   0.03272   0.02478  -0.0386   0.1479   1.0000
  11.250   1.4055   0.03456   0.02658  -0.0355   0.1365   1.0000
  11.500   1.4022   0.03676   0.02870  -0.0328   0.1259   1.0000
  11.750   1.3990   0.03914   0.03111  -0.0304   0.1152   1.0000
  12.000   1.3934   0.04178   0.03392  -0.0285   0.1040   1.0000
  12.250   1.3854   0.04481   0.03715  -0.0273   0.0924   1.0000
  12.500   1.3778   0.04813   0.04068  -0.0270   0.0810   1.0000
  12.750   1.3703   0.05179   0.04440  -0.0274   0.0732   1.0000
  13.000   1.3606   0.05595   0.04847  -0.0282   0.0685   1.0000
  13.250   1.3539   0.05975   0.05230  -0.0280   0.0640   1.0000
  13.500   1.3498   0.06309   0.05555  -0.0273   0.0604   1.0000
  13.750   1.3552   0.06533   0.05775  -0.0250   0.0568   1.0000
  14.000   1.3572   0.06835   0.06092  -0.0240   0.0541   1.0000
  14.250   1.3619   0.07105   0.06363  -0.0229   0.0514   1.0000
  14.500   1.3742   0.07359   0.06614  -0.0205   0.0485   1.0000
  14.750   1.3652   0.07800   0.07085  -0.0213   0.0476   1.0000
  15.000   1.3560   0.08267   0.07580  -0.0223   0.0469   1.0000
  15.250   1.3454   0.08766   0.08105  -0.0236   0.0464   1.0000
  15.500   1.3322   0.09316   0.08681  -0.0254   0.0460   1.0000
  15.750   1.3166   0.09925   0.09316  -0.0278   0.0459   1.0000
  16.000   1.2981   0.10607   0.10023  -0.0311   0.0459   1.0000
  16.250   1.2768   0.11379   0.10819  -0.0353   0.0460   1.0000
  16.500   1.2526   0.12254   0.11718  -0.0405   0.0464   1.0000
  16.750   1.2256   0.13249   0.12734  -0.0468   0.0470   1.0000
  17.000   1.1959   0.14385   0.13887  -0.0542   0.0477   1.0000
  17.250   1.1661   0.15624   0.15138  -0.0622   0.0486   1.0000
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