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GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 385 AIRFOIL (goe385-il)
Reynolds number: 200,000
Max Cl/Cd: 72.2 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe385-il-200000-n5.txt
Download as CSV file: xf-goe385-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 385 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3502   0.08833   0.08506  -0.0314   1.0000   0.0195
  -8.000  -0.3483   0.08530   0.08206  -0.0318   1.0000   0.0193
  -7.750  -0.3499   0.08224   0.07907  -0.0326   1.0000   0.0192
  -7.500  -0.3467   0.07835   0.07522  -0.0358   0.9968   0.0191
  -7.250  -0.3261   0.07457   0.07143  -0.0411   0.9869   0.0209
  -7.000  -0.3030   0.07059   0.06741  -0.0472   0.9763   0.0228
  -6.750  -0.2798   0.06490   0.06164  -0.0551   0.9640   0.0232
  -6.500  -0.2575   0.05911   0.05572  -0.0617   0.9507   0.0226
  -6.250  -0.2355   0.05366   0.05011  -0.0668   0.9360   0.0226
  -6.000  -0.2136   0.04872   0.04496  -0.0704   0.9199   0.0231
  -5.750  -0.1881   0.04285   0.03868  -0.0736   0.9035   0.0251
  -5.250  -0.1434   0.03398   0.02902  -0.0758   0.8731   0.0269
  -5.000  -0.1211   0.03313   0.02811  -0.0759   0.8585   0.0283
  -4.750  -0.0972   0.03124   0.02596  -0.0759   0.8449   0.0303
  -4.500  -0.0722   0.02837   0.02265  -0.0758   0.8322   0.0310
  -4.250  -0.0464   0.02601   0.01986  -0.0755   0.8199   0.0322
  -4.000  -0.0194   0.02443   0.01783  -0.0750   0.8076   0.0341
  -3.750   0.0073   0.02292   0.01591  -0.0747   0.7953   0.0346
  -3.500   0.0344   0.02187   0.01452  -0.0744   0.7829   0.0351
  -3.250   0.0601   0.01959   0.01195  -0.0744   0.7711   0.0368
  -3.000   0.0870   0.01859   0.01075  -0.0742   0.7587   0.0378
  -2.750   0.1143   0.01764   0.00957  -0.0740   0.7464   0.0381
  -2.500   0.1418   0.01683   0.00857  -0.0738   0.7329   0.0386
  -2.250   0.1690   0.01614   0.00771  -0.0734   0.7173   0.0392
  -2.000   0.1961   0.01555   0.00694  -0.0731   0.7000   0.0398
  -1.750   0.2231   0.01512   0.00637  -0.0728   0.6839   0.0414
  -1.500   0.2503   0.01470   0.00582  -0.0726   0.6714   0.0426
  -1.250   0.2776   0.01426   0.00528  -0.0723   0.6607   0.0430
  -1.000   0.3049   0.01388   0.00482  -0.0722   0.6509   0.0434
  -0.750   0.3322   0.01357   0.00443  -0.0720   0.6418   0.0440
  -0.500   0.3596   0.01331   0.00411  -0.0719   0.6326   0.0448
  -0.250   0.3872   0.01311   0.00385  -0.0718   0.6240   0.0457
   0.000   0.4148   0.01298   0.00364  -0.0717   0.6154   0.0467
   0.250   0.4426   0.01287   0.00347  -0.0717   0.6070   0.0478
   0.500   0.4703   0.01276   0.00329  -0.0717   0.5988   0.0522
   0.750   0.4982   0.01270   0.00321  -0.0717   0.5900   0.0564
   1.000   0.5260   0.01270   0.00313  -0.0717   0.5818   0.0608
   1.250   0.5528   0.01202   0.00316  -0.0719   0.5730   0.3156
   1.750   0.6073   0.01054   0.00321  -0.0712   0.5546   1.0000
   2.250   0.6619   0.01077   0.00330  -0.0711   0.5327   1.0000
   2.500   0.6890   0.01090   0.00335  -0.0709   0.5199   1.0000
   2.750   0.7160   0.01104   0.00341  -0.0708   0.5056   1.0000
   3.000   0.7428   0.01119   0.00350  -0.0706   0.4897   1.0000
   3.250   0.7694   0.01137   0.00359  -0.0705   0.4726   1.0000
   3.500   0.7957   0.01157   0.00371  -0.0703   0.4552   1.0000
   3.750   0.8219   0.01179   0.00386  -0.0701   0.4380   1.0000
   4.000   0.8479   0.01204   0.00403  -0.0698   0.4217   1.0000
   4.250   0.8738   0.01231   0.00423  -0.0696   0.4065   1.0000
   4.500   0.8995   0.01259   0.00446  -0.0694   0.3917   1.0000
   4.750   0.9250   0.01290   0.00471  -0.0691   0.3777   1.0000
   5.000   0.9506   0.01320   0.00498  -0.0689   0.3654   1.0000
   5.250   0.9759   0.01352   0.00527  -0.0686   0.3536   1.0000
   5.500   1.0010   0.01387   0.00559  -0.0683   0.3417   1.0000
   5.750   1.0257   0.01423   0.00592  -0.0680   0.3304   1.0000
   6.000   1.0508   0.01456   0.00626  -0.0677   0.3202   1.0000
   6.250   1.0758   0.01490   0.00663  -0.0674   0.3115   1.0000
   6.500   1.1003   0.01527   0.00701  -0.0670   0.3034   1.0000
   6.750   1.1253   0.01559   0.00739  -0.0667   0.2956   1.0000
   7.000   1.1492   0.01599   0.00780  -0.0663   0.2861   1.0000
   7.250   1.1728   0.01638   0.00822  -0.0658   0.2729   1.0000
   7.500   1.1960   0.01679   0.00865  -0.0653   0.2581   1.0000
   7.750   1.2190   0.01720   0.00909  -0.0648   0.2440   1.0000
   8.000   1.2410   0.01768   0.00957  -0.0642   0.2273   1.0000
   8.250   1.2617   0.01827   0.01012  -0.0634   0.2006   1.0000
   8.500   1.2799   0.01905   0.01077  -0.0623   0.1645   1.0000
   8.750   1.2923   0.02033   0.01176  -0.0606   0.1244   1.0000
   9.000   1.3058   0.02150   0.01281  -0.0590   0.1021   1.0000
   9.250   1.3163   0.02284   0.01397  -0.0570   0.0618   1.0000
   9.500   1.3242   0.02427   0.01534  -0.0546   0.0423   1.0000
  10.000   1.3336   0.02709   0.01810  -0.0491   0.0193   1.0000
  10.250   1.3390   0.02852   0.01962  -0.0467   0.0173   1.0000
  10.500   1.3435   0.03010   0.02134  -0.0445   0.0160   1.0000
  10.750   1.3497   0.03164   0.02305  -0.0428   0.0154   1.0000
  11.000   1.3542   0.03342   0.02500  -0.0413   0.0148   1.0000
  11.250   1.3570   0.03546   0.02720  -0.0400   0.0142   1.0000
  11.500   1.3582   0.03779   0.02972  -0.0389   0.0135   1.0000
  11.750   1.3574   0.04043   0.03251  -0.0381   0.0130   1.0000
  12.000   1.3546   0.04344   0.03567  -0.0376   0.0125   1.0000
  12.250   1.3493   0.04689   0.03927  -0.0374   0.0120   1.0000
  12.500   1.3418   0.05078   0.04331  -0.0375   0.0117   1.0000
  12.750   1.3325   0.05501   0.04768  -0.0378   0.0115   1.0000
  13.000   1.3224   0.05943   0.05223  -0.0383   0.0113   1.0000
  13.250   1.3159   0.06343   0.05636  -0.0388   0.0112   1.0000
  13.500   1.3109   0.06731   0.06037  -0.0393   0.0110   1.0000
  13.750   1.3058   0.07130   0.06449  -0.0399   0.0109   1.0000
  14.000   1.3008   0.07533   0.06865  -0.0406   0.0107   1.0000
  14.250   1.2962   0.07939   0.07283  -0.0413   0.0106   1.0000
  14.500   1.2922   0.08342   0.07698  -0.0421   0.0104   1.0000
  14.750   1.2885   0.08741   0.08108  -0.0428   0.0103   1.0000
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