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GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 200,000
Max Cl/Cd: 65.22 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe285-il-200000-n5.txt
Download as CSV file: xf-goe285-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 285 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3871   0.08932   0.08546  -0.0368   1.0000   0.0360
  -9.000  -0.3938   0.08481   0.08099  -0.0385   1.0000   0.0357
  -8.750  -0.4066   0.08006   0.07630  -0.0401   1.0000   0.0353
  -8.500  -0.5499   0.04633   0.04208  -0.0590   0.9952   0.0336
  -8.250  -0.5329   0.04121   0.03664  -0.0630   0.9884   0.0340
  -8.000  -0.5098   0.03736   0.03248  -0.0661   0.9833   0.0346
  -7.750  -0.4909   0.03296   0.02759  -0.0681   0.9755   0.0351
  -7.500  -0.4676   0.02914   0.02323  -0.0698   0.9694   0.0354
  -7.250  -0.4415   0.02660   0.02028  -0.0708   0.9627   0.0359
  -7.000  -0.4119   0.02459   0.01790  -0.0721   0.9579   0.0363
  -6.750  -0.3852   0.02303   0.01606  -0.0724   0.9501   0.0368
  -6.500  -0.3533   0.02163   0.01437  -0.0736   0.9452   0.0373
  -6.250  -0.3254   0.02055   0.01306  -0.0738   0.9358   0.0380
  -6.000  -0.2919   0.01951   0.01182  -0.0750   0.9293   0.0388
  -5.750  -0.2632   0.01867   0.01093  -0.0753   0.9185   0.0395
  -5.500  -0.2319   0.01792   0.01011  -0.0760   0.9088   0.0402
  -5.250  -0.2006   0.01722   0.00933  -0.0766   0.8985   0.0409
  -5.000  -0.1714   0.01659   0.00861  -0.0767   0.8863   0.0416
  -4.750  -0.1419   0.01601   0.00794  -0.0768   0.8739   0.0425
  -4.500  -0.1128   0.01549   0.00730  -0.0769   0.8615   0.0435
  -4.250  -0.0850   0.01503   0.00675  -0.0766   0.8489   0.0445
  -4.000  -0.0578   0.01464   0.00635  -0.0764   0.8372   0.0459
  -3.750  -0.0301   0.01434   0.00600  -0.0761   0.8263   0.0480
  -3.500  -0.0030   0.01404   0.00562  -0.0757   0.8144   0.0505
  -3.250   0.0239   0.01377   0.00535  -0.0754   0.8023   0.0532
  -3.000   0.0509   0.01353   0.00504  -0.0749   0.7894   0.0574
  -2.750   0.0779   0.01332   0.00481  -0.0745   0.7764   0.0638
  -2.500   0.1045   0.01313   0.00459  -0.0741   0.7613   0.0728
  -2.250   0.1311   0.01296   0.00439  -0.0736   0.7451   0.0827
  -2.000   0.1577   0.01283   0.00421  -0.0731   0.7283   0.0925
  -1.750   0.1843   0.01274   0.00405  -0.0727   0.7114   0.1014
  -1.500   0.2109   0.01264   0.00392  -0.0722   0.6946   0.1109
  -1.250   0.2374   0.01257   0.00380  -0.0717   0.6772   0.1213
  -1.000   0.2637   0.01251   0.00368  -0.0713   0.6597   0.1331
  -0.750   0.2901   0.01246   0.00358  -0.0708   0.6428   0.1479
  -0.500   0.3164   0.01236   0.00349  -0.0704   0.6276   0.1668
  -0.250   0.3428   0.01225   0.00341  -0.0700   0.6141   0.1930
   0.000   0.3686   0.01207   0.00336  -0.0696   0.6003   0.2432
   0.250   0.3927   0.01163   0.00334  -0.0690   0.5860   0.3867
   0.500   0.4122   0.01087   0.00338  -0.0673   0.5712   0.6385
   0.750   0.4537   0.01041   0.00356  -0.0690   0.5523   0.9358
   1.000   0.5133   0.01056   0.00356  -0.0756   0.5280   1.0000
   1.250   0.5372   0.01071   0.00356  -0.0747   0.5090   1.0000
   1.500   0.5609   0.01088   0.00358  -0.0738   0.4909   1.0000
   1.750   0.5844   0.01106   0.00362  -0.0728   0.4740   1.0000
   2.000   0.6080   0.01126   0.00369  -0.0719   0.4586   1.0000
   2.250   0.6317   0.01146   0.00377  -0.0710   0.4447   1.0000
   2.500   0.6555   0.01168   0.00388  -0.0702   0.4320   1.0000
   3.000   0.7034   0.01212   0.00414  -0.0685   0.4083   1.0000
   3.250   0.7276   0.01235   0.00429  -0.0678   0.3974   1.0000
   3.500   0.7515   0.01259   0.00446  -0.0670   0.3863   1.0000
   3.750   0.7761   0.01280   0.00463  -0.0663   0.3752   1.0000
   4.000   0.8003   0.01305   0.00482  -0.0656   0.3647   1.0000
   4.250   0.8245   0.01330   0.00501  -0.0649   0.3539   1.0000
   4.500   0.8489   0.01354   0.00523  -0.0642   0.3435   1.0000
   4.750   0.8728   0.01382   0.00545  -0.0635   0.3340   1.0000
   5.000   0.8971   0.01407   0.00568  -0.0628   0.3241   1.0000
   5.250   0.9209   0.01436   0.00593  -0.0621   0.3148   1.0000
   5.500   0.9445   0.01467   0.00619  -0.0614   0.3052   1.0000
   5.750   0.9682   0.01497   0.00646  -0.0607   0.2960   1.0000
   6.000   0.9910   0.01532   0.00675  -0.0598   0.2869   1.0000
   6.250   1.0147   0.01562   0.00705  -0.0592   0.2783   1.0000
   6.750   1.0613   0.01629   0.00771  -0.0577   0.2666   1.0000
   7.000   1.0844   0.01663   0.00806  -0.0570   0.2608   1.0000
   7.250   1.1067   0.01702   0.00842  -0.0561   0.2553   1.0000
   7.500   1.1302   0.01733   0.00880  -0.0555   0.2501   1.0000
   7.750   1.1529   0.01768   0.00919  -0.0547   0.2451   1.0000
   8.000   1.1741   0.01812   0.00960  -0.0537   0.2401   1.0000
   8.250   1.1972   0.01842   0.01000  -0.0530   0.2336   1.0000
   8.500   1.2181   0.01884   0.01044  -0.0520   0.2269   1.0000
   8.750   1.2394   0.01923   0.01088  -0.0510   0.2212   1.0000
   9.000   1.2607   0.01960   0.01133  -0.0501   0.2142   1.0000
   9.250   1.2801   0.02006   0.01182  -0.0489   0.2064   1.0000
   9.500   1.2997   0.02048   0.01230  -0.0478   0.1950   1.0000
   9.750   1.3185   0.02094   0.01280  -0.0465   0.1781   1.0000
  10.000   1.3237   0.02205   0.01356  -0.0435   0.1258   1.0000
  10.250   1.3282   0.02335   0.01473  -0.0405   0.1056   1.0000
  10.500   1.3355   0.02455   0.01590  -0.0380   0.0915   1.0000
  10.750   1.3436   0.02571   0.01706  -0.0357   0.0769   1.0000
  11.000   1.3494   0.02705   0.01837  -0.0334   0.0623   1.0000
  11.250   1.3546   0.02849   0.01979  -0.0313   0.0539   1.0000
  11.500   1.3602   0.02996   0.02130  -0.0294   0.0499   1.0000
  11.750   1.3646   0.03158   0.02298  -0.0277   0.0472   1.0000
  12.000   1.3682   0.03337   0.02485  -0.0262   0.0453   1.0000
  12.250   1.3719   0.03524   0.02682  -0.0250   0.0438   1.0000
  12.500   1.3740   0.03736   0.02905  -0.0239   0.0425   1.0000
  12.750   1.3740   0.03979   0.03158  -0.0230   0.0414   1.0000
  13.000   1.3720   0.04257   0.03447  -0.0224   0.0406   1.0000
  13.250   1.3676   0.04574   0.03775  -0.0221   0.0398   1.0000
  13.500   1.3636   0.04902   0.04114  -0.0221   0.0392   1.0000
  13.750   1.3608   0.05229   0.04455  -0.0222   0.0386   1.0000
  14.000   1.3565   0.05581   0.04820  -0.0225   0.0380   1.0000
  14.250   1.3511   0.05959   0.05211  -0.0230   0.0374   1.0000
  14.500   1.3449   0.06356   0.05620  -0.0237   0.0369   1.0000
  14.750   1.3381   0.06772   0.06047  -0.0245   0.0363   1.0000
  15.000   1.3313   0.07199   0.06486  -0.0254   0.0358   1.0000
  15.250   1.3242   0.07636   0.06933  -0.0265   0.0353   1.0000
  15.500   1.3174   0.08071   0.07376  -0.0276   0.0349   1.0000
  15.750   1.3109   0.08502   0.07814  -0.0287   0.0344   1.0000
  16.000   1.3053   0.08913   0.08229  -0.0296   0.0340   1.0000
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