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GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 574 AIRFOIL (goe574-il)
Reynolds number: 500,000
Max Cl/Cd: 97.31 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe574-il-500000-n5.txt
Download as CSV file: xf-goe574-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 574 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2428   0.08735   0.08516  -0.0578   0.9813   0.0068
  -8.250  -0.2315   0.08419   0.08201  -0.0607   0.9780   0.0058
  -8.000  -0.2347   0.07967   0.07752  -0.0626   0.9714   0.0068
  -7.500  -0.2624   0.07536   0.07330  -0.0576   0.9226   0.0067
  -7.250  -0.2327   0.06814   0.06600  -0.0688   0.9022   0.0067
  -7.000  -0.1900   0.05870   0.05641  -0.0850   0.8859   0.0067
  -6.750  -0.1372   0.04569   0.04305  -0.1054   0.8645   0.0072
  -6.500  -0.0865   0.03677   0.03364  -0.1187   0.8356   0.0076
  -6.250  -0.0710   0.03028   0.02666  -0.1202   0.8097   0.0082
  -6.000  -0.0849   0.02036   0.01578  -0.1143   0.7926   0.0092
  -5.750  -0.0835   0.01503   0.00943  -0.1095   0.7773   0.0105
  -5.500  -0.0603   0.01473   0.00895  -0.1086   0.7601   0.0114
  -5.250  -0.0366   0.01473   0.00883  -0.1078   0.7435   0.0122
  -5.000  -0.0142   0.01440   0.00830  -0.1066   0.7276   0.0137
  -4.750   0.0071   0.01366   0.00726  -0.1052   0.7124   0.0155
  -4.500   0.0298   0.01364   0.00716  -0.1042   0.6966   0.0165
  -4.250   0.0528   0.01369   0.00713  -0.1033   0.6807   0.0177
  -4.000   0.0753   0.01348   0.00675  -0.1021   0.6652   0.0195
  -3.750   0.0983   0.01335   0.00645  -0.1011   0.6496   0.0217
  -3.500   0.1215   0.01325   0.00618  -0.1001   0.6345   0.0231
  -3.250   0.1450   0.01330   0.00608  -0.0991   0.6192   0.0238
  -3.000   0.1658   0.01233   0.00495  -0.0978   0.6046   0.0259
  -2.750   0.1883   0.01204   0.00455  -0.0968   0.5896   0.0271
  -2.500   0.2112   0.01183   0.00423  -0.0957   0.5747   0.0286
  -2.250   0.2340   0.01162   0.00390  -0.0947   0.5603   0.0299
  -2.000   0.2570   0.01139   0.00357  -0.0937   0.5473   0.0306
  -1.750   0.2800   0.01122   0.00329  -0.0927   0.5353   0.0313
  -1.500   0.3030   0.01107   0.00305  -0.0916   0.5239   0.0317
  -1.000   0.3494   0.01083   0.00265  -0.0898   0.5035   0.0325
  -0.750   0.3729   0.01076   0.00251  -0.0889   0.4952   0.0330
  -0.500   0.3963   0.01067   0.00236  -0.0880   0.4871   0.0331
  -0.250   0.4199   0.01061   0.00223  -0.0871   0.4802   0.0330
   0.000   0.4438   0.01056   0.00212  -0.0863   0.4738   0.0330
   0.250   0.4674   0.01054   0.00204  -0.0855   0.4677   0.0331
   0.500   0.4917   0.01053   0.00198  -0.0848   0.4623   0.0331
   0.750   0.5156   0.01053   0.00193  -0.0840   0.4574   0.0335
   1.000   0.5396   0.01055   0.00191  -0.0832   0.4533   0.0337
   1.250   0.5640   0.01055   0.00189  -0.0825   0.4497   0.0351
   1.500   0.5878   0.01055   0.00190  -0.0817   0.4459   0.0431
   1.750   0.6090   0.01035   0.00199  -0.0805   0.4427   0.1644
   2.250   0.8248   0.00953   0.00311  -0.1182   0.4332   1.0000
   2.500   0.8472   0.00962   0.00319  -0.1172   0.4304   1.0000
   2.750   0.8692   0.00974   0.00328  -0.1160   0.4275   1.0000
   3.000   0.8912   0.00985   0.00338  -0.1149   0.4243   1.0000
   3.250   0.9137   0.00993   0.00348  -0.1139   0.4206   1.0000
   3.500   0.9355   0.01003   0.00359  -0.1127   0.4163   1.0000
   3.750   0.9560   0.01018   0.00370  -0.1113   0.4098   1.0000
   4.000   0.9772   0.01026   0.00382  -0.1100   0.4013   1.0000
   4.250   0.9974   0.01041   0.00394  -0.1085   0.3947   1.0000
   4.500   1.0184   0.01050   0.00406  -0.1072   0.3863   1.0000
   4.750   1.0373   0.01066   0.00418  -0.1054   0.3705   1.0000
   5.000   1.0552   0.01086   0.00432  -0.1035   0.3484   1.0000
   5.250   1.0605   0.01171   0.00468  -0.0992   0.2569   1.0000
   5.500   1.0563   0.01320   0.00559  -0.0933   0.1552   1.0000
   5.750   1.0430   0.01480   0.00662  -0.0854   0.0256   1.0000
   6.000   1.0553   0.01515   0.00697  -0.0823   0.0167   1.0000
   6.250   1.0693   0.01545   0.00733  -0.0796   0.0147   1.0000
   6.500   1.0819   0.01581   0.00777  -0.0767   0.0125   1.0000
   6.750   1.0930   0.01627   0.00831  -0.0735   0.0107   1.0000
   7.000   1.1026   0.01682   0.00897  -0.0700   0.0096   1.0000
   7.250   1.1161   0.01720   0.00940  -0.0674   0.0087   1.0000
   7.500   1.1280   0.01768   0.00994  -0.0646   0.0080   1.0000
   7.750   1.1376   0.01828   0.01061  -0.0614   0.0076   1.0000
   8.000   1.1474   0.01889   0.01128  -0.0583   0.0071   1.0000
   8.250   1.1543   0.01965   0.01213  -0.0549   0.0067   1.0000
   8.500   1.1575   0.02062   0.01320  -0.0510   0.0064   1.0000
   8.750   1.1590   0.02172   0.01440  -0.0470   0.0061   1.0000
   9.000   1.1622   0.02281   0.01558  -0.0435   0.0060   1.0000
   9.250   1.1647   0.02400   0.01687  -0.0401   0.0057   1.0000
   9.500   1.1746   0.02483   0.01776  -0.0381   0.0052   1.0000
   9.750   1.1704   0.02664   0.01970  -0.0345   0.0052   1.0000
  10.000   1.1850   0.02730   0.02038  -0.0334   0.0046   1.0000
  10.250   1.1779   0.02963   0.02284  -0.0303   0.0047   1.0000
  10.500   1.1865   0.03089   0.02414  -0.0291   0.0044   1.0000
  10.750   1.1857   0.03303   0.02637  -0.0272   0.0043   1.0000
  11.000   1.1775   0.03595   0.02938  -0.0252   0.0040   1.0000
  11.250   1.1766   0.03835   0.03189  -0.0238   0.0040   1.0000
  11.500   1.1780   0.04058   0.03424  -0.0226   0.0039   1.0000
  11.750   1.1784   0.04295   0.03671  -0.0213   0.0038   1.0000
  12.000   1.1791   0.04530   0.03917  -0.0198   0.0037   1.0000
  12.250   1.1813   0.04749   0.04145  -0.0185   0.0037   1.0000
  12.500   1.1854   0.04954   0.04362  -0.0169   0.0036   1.0000
  12.750   1.1912   0.05149   0.04569  -0.0153   0.0035   1.0000
  13.000   1.1985   0.05341   0.04775  -0.0134   0.0034   1.0000
  13.250   1.2051   0.05549   0.04996  -0.0121   0.0034   1.0000
  13.500   1.2112   0.05789   0.05254  -0.0105   0.0033   1.0000
  13.750   1.2139   0.06056   0.05537  -0.0095   0.0031   1.0000
  14.000   1.2145   0.06330   0.05826  -0.0090   0.0030   1.0000
  14.250   1.2127   0.06690   0.06208  -0.0079   0.0031   1.0000
  14.500   1.2098   0.06962   0.06486  -0.0088   0.0028   1.0000
  14.750   1.2059   0.07309   0.06846  -0.0090   0.0028   1.0000
  15.000   1.2025   0.07617   0.07161  -0.0102   0.0026   1.0000
  15.250   1.1941   0.08070   0.07635  -0.0102   0.0027   1.0000
  15.500   1.1886   0.08452   0.08031  -0.0114   0.0026   1.0000
  15.750   1.1690   0.09138   0.08751  -0.0114   0.0027   1.0000
  16.000   1.1698   0.09399   0.09009  -0.0138   0.0026   1.0000
  16.250   1.1556   0.09984   0.09615  -0.0152   0.0026   1.0000
  16.500   1.1464   0.10480   0.10121  -0.0174   0.0025   1.0000
  16.750   1.1283   0.11181   0.10846  -0.0195   0.0026   1.0000
  17.000   1.1136   0.11825   0.11504  -0.0223   0.0026   1.0000
  17.250   1.1030   0.12394   0.12082  -0.0255   0.0025   1.0000
  17.500   1.0861   0.13147   0.12854  -0.0287   0.0025   1.0000
  17.750   1.0751   0.13782   0.13499  -0.0323   0.0025   1.0000
  18.000   1.0463   0.14935   0.14676  -0.0379   0.0026   1.0000
  18.250   1.0412   0.15490   0.15237  -0.0415   0.0025   1.0000
  18.500   1.0267   0.16347   0.16102  -0.0466   0.0025   1.0000
  18.750   0.9700   0.19160   0.18938  -0.0600   0.0029   1.0000
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