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GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 57 AIRFOIL (goe57-il)
Reynolds number: 50,000
Max Cl/Cd: 41.63 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe57-il-50000.txt
Download as CSV file: xf-goe57-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 57 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3187   0.11047   0.10364  -0.0235   1.0000   0.1084
  -8.000  -0.3260   0.11031   0.10362  -0.0243   1.0000   0.1104
  -7.750  -0.3352   0.11098   0.10446  -0.0266   1.0000   0.1112
  -7.500  -0.3157   0.10300   0.09644  -0.0227   1.0000   0.1163
  -7.250  -0.3155   0.10088   0.09441  -0.0222   1.0000   0.1208
  -7.000  -0.3196   0.10025   0.09391  -0.0240   1.0000   0.1243
  -6.750  -0.3240   0.10134   0.09512  -0.0296   1.0000   0.1256
  -6.500  -0.3145   0.09415   0.08796  -0.0226   1.0000   0.1296
  -6.250  -0.3124   0.09174   0.08561  -0.0219   1.0000   0.1342
  -6.000  -0.3123   0.09101   0.08495  -0.0250   1.0000   0.1390
  -5.750  -0.3096   0.08835   0.08236  -0.0258   1.0000   0.1414
  -5.500  -0.3066   0.08479   0.07886  -0.0222   1.0000   0.1461
  -5.250  -0.2977   0.08391   0.07796  -0.0274   1.0000   0.1540
  -4.750  -0.2786   0.07895   0.07301  -0.0310   1.0000   0.1696
  -4.500  -0.2798   0.07472   0.06890  -0.0251   1.0000   0.1748
  -4.000  -0.2458   0.07017   0.06421  -0.0327   1.0000   0.1986
  -3.750  -0.2420   0.06668   0.06082  -0.0291   1.0000   0.2064
  -3.500  -0.2267   0.06397   0.05809  -0.0306   1.0000   0.2205
  -3.250  -0.2038   0.06161   0.05564  -0.0348   1.0000   0.2423
  -3.000  -0.1943   0.05865   0.05274  -0.0332   1.0000   0.2606
  -2.750  -0.1806   0.05612   0.05022  -0.0331   1.0000   0.2907
  -2.500  -0.1676   0.05368   0.04779  -0.0327   1.0000   0.3320
  -1.500  -0.1471   0.04418   0.03872  -0.0164   1.0000   0.5535
  -1.250  -0.1394   0.04176   0.03639  -0.0126   1.0000   0.5996
  -1.000  -0.1195   0.03962   0.03425  -0.0124   1.0000   0.6408
  -0.750  -0.0988   0.03744   0.03210  -0.0124   1.0000   0.6722
  -0.500  -0.0672   0.03553   0.03018  -0.0155   1.0000   0.6937
  -0.250   0.0810   0.03595   0.02954  -0.0534   1.0000   0.5350
   0.250   0.2066   0.03688   0.02846  -0.0739   1.0000   0.2482
   0.500   0.2775   0.03646   0.02732  -0.0820   0.9870   0.2108
   0.750   0.3424   0.03587   0.02624  -0.0890   0.9729   0.1971
   1.000   0.4041   0.03513   0.02520  -0.0954   0.9580   0.1888
   1.250   0.4596   0.03469   0.02439  -0.1003   0.9400   0.1869
   1.500   0.5155   0.03416   0.02361  -0.1048   0.9199   0.1993
   1.750   0.5806   0.03300   0.02241  -0.1101   0.9003   0.2168
   2.000   0.6287   0.03197   0.02149  -0.1125   0.8760   0.2476
   2.250   0.6903   0.02881   0.01975  -0.1156   0.8564   1.0000
   2.500   0.7330   0.02826   0.01869  -0.1157   0.8308   1.0000
   2.750   0.7758   0.02748   0.01776  -0.1159   0.8077   1.0000
   3.000   0.8134   0.02685   0.01705  -0.1154   0.7853   1.0000
   3.250   0.8454   0.02642   0.01658  -0.1142   0.7614   1.0000
   3.500   0.8819   0.02561   0.01576  -0.1132   0.7389   1.0000
   3.750   0.9111   0.02512   0.01523  -0.1113   0.7110   1.0000
   4.000   0.9413   0.02453   0.01457  -0.1094   0.6813   1.0000
   4.250   0.9681   0.02426   0.01420  -0.1072   0.6461   1.0000
   4.500   0.9959   0.02412   0.01389  -0.1051   0.6086   1.0000
   4.750   1.0196   0.02449   0.01406  -0.1029   0.5672   1.0000
   5.000   1.0434   0.02510   0.01445  -0.1011   0.5290   1.0000
   5.250   1.0673   0.02593   0.01510  -0.0998   0.4970   1.0000
   5.500   1.0931   0.02688   0.01591  -0.0989   0.4736   1.0000
   5.750   1.1173   0.02805   0.01711  -0.0982   0.4548   1.0000
   6.000   1.1425   0.02927   0.01836  -0.0977   0.4410   1.0000
   6.250   1.1693   0.03047   0.01955  -0.0975   0.4307   1.0000
   6.500   1.1915   0.03201   0.02141  -0.0969   0.4214   1.0000
   6.750   1.2164   0.03345   0.02298  -0.0966   0.4146   1.0000
   7.000   1.2380   0.03477   0.02451  -0.0958   0.4048   1.0000
   7.250   1.2589   0.03565   0.02550  -0.0946   0.3908   1.0000
   7.500   1.2822   0.03579   0.02551  -0.0931   0.3721   1.0000
   7.750   1.3031   0.03643   0.02629  -0.0918   0.3577   1.0000
   8.000   1.3205   0.03754   0.02774  -0.0903   0.3464   1.0000
   8.250   1.3410   0.03781   0.02809  -0.0888   0.3304   1.0000
   8.500   1.3603   0.03811   0.02853  -0.0871   0.3151   1.0000
   8.750   1.3708   0.03786   0.02845  -0.0841   0.2914   1.0000
   9.000   1.3761   0.03718   0.02785  -0.0803   0.2625   1.0000
   9.250   1.3782   0.03717   0.02800  -0.0763   0.2367   1.0000
   9.500   1.3732   0.03773   0.02873  -0.0718   0.2058   1.0000
   9.750   1.3632   0.03929   0.03013  -0.0673   0.1703   1.0000
  10.000   1.3568   0.04145   0.03242  -0.0634   0.1304   1.0000
  10.250   1.3539   0.04376   0.03454  -0.0605   0.1049   1.0000
  10.500   1.3485   0.04655   0.03708  -0.0581   0.0950   1.0000
  10.750   1.3437   0.04963   0.04009  -0.0560   0.0885   1.0000
  11.000   1.3378   0.05295   0.04335  -0.0542   0.0840   1.0000
  11.250   1.3362   0.05613   0.04659  -0.0524   0.0803   1.0000
  11.500   1.3400   0.05901   0.04968  -0.0506   0.0772   1.0000
  11.750   1.3475   0.06175   0.05255  -0.0487   0.0745   1.0000
  12.000   1.3627   0.06430   0.05522  -0.0466   0.0719   1.0000
  12.250   1.3940   0.06754   0.05851  -0.0447   0.0697   1.0000
  12.500   1.3953   0.07137   0.06272  -0.0434   0.0693   1.0000
  12.750   1.3894   0.07561   0.06733  -0.0424   0.0690   1.0000
  13.000   1.3785   0.08028   0.07232  -0.0420   0.0689   1.0000
  13.250   1.3640   0.08542   0.07778  -0.0423   0.0689   1.0000
  13.500   1.3465   0.09111   0.08374  -0.0433   0.0691   1.0000
  13.750   1.3277   0.09733   0.09022  -0.0451   0.0694   1.0000
  14.000   1.3083   0.10409   0.09719  -0.0477   0.0697   1.0000
  14.250   1.2436   0.11857   0.11219  -0.0598   0.0729   1.0000
  14.500   1.1600   0.14506   0.13880  -0.0793   0.0791   1.0000
  14.750   1.1426   0.15619   0.14986  -0.0852   0.0810   1.0000
  15.000   1.1363   0.16420   0.15783  -0.0888   0.0819   1.0000
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