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GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 374 AIRFOIL (goe374-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.42 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe374-il-1000000-n5.txt
Download as CSV file: xf-goe374-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 374 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3216   0.09572   0.09417  -0.0180   1.0000   0.0042
  -8.000  -0.3181   0.09299   0.09147  -0.0186   1.0000   0.0042
  -7.750  -0.3166   0.09027   0.08877  -0.0189   1.0000   0.0042
  -7.500  -0.3112   0.08738   0.08590  -0.0202   0.9935   0.0042
  -7.250  -0.2957   0.08338   0.08190  -0.0250   0.9807   0.0042
  -7.000  -0.2700   0.07877   0.07729  -0.0323   0.9695   0.0040
  -6.750  -0.2343   0.07322   0.07169  -0.0429   0.9567   0.0039
  -6.250  -0.1740   0.06385   0.06211  -0.0589   0.9022   0.0039
  -6.000  -0.1581   0.06136   0.05950  -0.0613   0.8745   0.0051
  -5.000  -0.0826   0.04679   0.04443  -0.0718   0.8011   0.0041
  -4.750  -0.0602   0.04320   0.04069  -0.0738   0.7838   0.0040
  -4.500  -0.0368   0.03991   0.03723  -0.0754   0.7617   0.0039
  -4.250  -0.0125   0.03639   0.03349  -0.0766   0.7348   0.0039
  -4.000   0.0124   0.03239   0.02919  -0.0774   0.7012   0.0041
  -3.750   0.0378   0.02802   0.02447  -0.0777   0.6721   0.0044
  -3.500   0.0623   0.02629   0.02251  -0.0776   0.6477   0.0047
  -3.250   0.0878   0.02367   0.01962  -0.0773   0.6311   0.0049
  -3.000   0.1135   0.02131   0.01698  -0.0768   0.6171   0.0056
  -2.500   0.1639   0.01362   0.00827  -0.0741   0.5957   0.0075
  -2.250   0.1900   0.01258   0.00702  -0.0735   0.5831   0.0086
  -2.000   0.2159   0.01128   0.00547  -0.0729   0.5702   0.0102
  -1.750   0.2425   0.01118   0.00527  -0.0726   0.5535   0.0114
  -1.500   0.2676   0.00975   0.00353  -0.0718   0.5352   0.0147
  -1.250   0.2944   0.01007   0.00377  -0.0716   0.5080   0.0153
  -1.000   0.3206   0.01027   0.00385  -0.0713   0.4794   0.0163
  -0.750   0.3468   0.01020   0.00363  -0.0709   0.4571   0.0177
  -0.500   0.3732   0.01009   0.00340  -0.0705   0.4409   0.0196
  -0.250   0.3994   0.00995   0.00313  -0.0701   0.4237   0.0208
   0.250   0.4519   0.00960   0.00261  -0.0695   0.4006   0.0230
   0.500   0.4780   0.00940   0.00239  -0.0691   0.3920   0.0241
   0.750   0.5044   0.00927   0.00224  -0.0688   0.3827   0.0251
   1.000   0.5307   0.00919   0.00211  -0.0685   0.3727   0.0259
   1.250   0.5571   0.00910   0.00198  -0.0682   0.3640   0.0263
   1.500   0.5835   0.00904   0.00188  -0.0679   0.3560   0.0266
   1.750   0.6098   0.00902   0.00182  -0.0676   0.3461   0.0273
   2.000   0.6363   0.00897   0.00174  -0.0673   0.3383   0.0272
   2.250   0.6627   0.00896   0.00169  -0.0670   0.3293   0.0268
   2.500   0.6890   0.00897   0.00166  -0.0668   0.3187   0.0265
   2.750   0.7153   0.00900   0.00165  -0.0665   0.3075   0.0263
   3.000   0.7416   0.00905   0.00166  -0.0662   0.2964   0.0261
   3.250   0.7678   0.00913   0.00170  -0.0659   0.2855   0.0260
   3.500   0.7940   0.00921   0.00175  -0.0656   0.2750   0.0259
   3.750   0.8201   0.00931   0.00181  -0.0653   0.2647   0.0261
   4.000   0.8462   0.00942   0.00190  -0.0651   0.2545   0.0265
   4.250   0.8721   0.00957   0.00200  -0.0648   0.2436   0.0276
   4.500   0.8980   0.00971   0.00212  -0.0645   0.2323   0.0298
   4.750   0.9237   0.00989   0.00227  -0.0641   0.2195   0.0339
   5.000   0.9640   0.00873   0.00278  -0.0680   0.1885   1.0000
   5.250   0.9878   0.00908   0.00302  -0.0674   0.1646   1.0000
   5.500   1.0101   0.00960   0.00334  -0.0665   0.1318   1.0000
   5.750   1.0338   0.00997   0.00362  -0.0659   0.1156   1.0000
   6.000   1.0576   0.01031   0.00391  -0.0653   0.1032   1.0000
   6.250   1.0810   0.01069   0.00421  -0.0647   0.0860   1.0000
   6.500   1.0964   0.01202   0.00513  -0.0629   0.0156   1.0000
   6.750   1.1203   0.01235   0.00549  -0.0622   0.0098   1.0000
   7.000   1.1438   0.01271   0.00590  -0.0616   0.0079   1.0000
   7.250   1.1670   0.01310   0.00633  -0.0609   0.0062   1.0000
   7.500   1.1902   0.01347   0.00673  -0.0602   0.0052   1.0000
   7.750   1.2122   0.01396   0.00726  -0.0594   0.0043   1.0000
   8.000   1.2348   0.01437   0.00773  -0.0586   0.0038   1.0000
   8.250   1.2567   0.01485   0.00828  -0.0578   0.0035   1.0000
   8.500   1.2783   0.01535   0.00883  -0.0569   0.0032   1.0000
   8.750   1.2989   0.01592   0.00946  -0.0559   0.0029   1.0000
   9.000   1.3181   0.01663   0.01026  -0.0546   0.0025   1.0000
   9.250   1.3385   0.01717   0.01086  -0.0536   0.0023   1.0000
   9.500   1.3571   0.01786   0.01164  -0.0524   0.0022   1.0000
   9.750   1.3752   0.01855   0.01241  -0.0510   0.0020   1.0000
  10.000   1.3915   0.01936   0.01334  -0.0495   0.0019   1.0000
  10.250   1.4074   0.02014   0.01420  -0.0479   0.0018   1.0000
  10.500   1.4225   0.02093   0.01506  -0.0463   0.0017   1.0000
  10.750   1.4343   0.02190   0.01612  -0.0442   0.0016   1.0000
  11.000   1.4411   0.02299   0.01733  -0.0412   0.0015   1.0000
  11.250   1.4424   0.02421   0.01867  -0.0375   0.0014   1.0000
  11.500   1.4423   0.02559   0.02018  -0.0340   0.0014   1.0000
  11.750   1.4423   0.02709   0.02180  -0.0310   0.0014   1.0000
  12.000   1.4448   0.02854   0.02337  -0.0287   0.0013   1.0000
  12.250   1.4439   0.03040   0.02535  -0.0265   0.0013   1.0000
  12.500   1.4388   0.03282   0.02791  -0.0246   0.0013   1.0000
  12.750   1.4345   0.03546   0.03069  -0.0234   0.0012   1.0000
  13.000   1.4260   0.03883   0.03422  -0.0227   0.0012   1.0000
  13.250   1.4227   0.04198   0.03750  -0.0227   0.0011   1.0000
  13.500   1.4123   0.04632   0.04201  -0.0234   0.0011   1.0000
  13.750   1.4036   0.05071   0.04655  -0.0244   0.0011   1.0000
  14.000   1.3952   0.05521   0.05118  -0.0257   0.0011   1.0000
  14.250   1.3890   0.05958   0.05567  -0.0272   0.0011   1.0000
  14.500   1.3724   0.06553   0.06177  -0.0292   0.0011   1.0000
  14.750   1.3589   0.07124   0.06761  -0.0312   0.0011   1.0000
  15.000   1.3480   0.07677   0.07328  -0.0334   0.0010   1.0000
  15.250   1.3389   0.08210   0.07872  -0.0357   0.0010   1.0000
  15.500   1.3240   0.08851   0.08526  -0.0383   0.0010   1.0000
  15.750   1.3098   0.09497   0.09184  -0.0410   0.0010   1.0000
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