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GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 480 AIRFOIL (goe480-il)
Reynolds number: 200,000
Max Cl/Cd: 79.02 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe480-il-200000.txt
Download as CSV file: xf-goe480-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 480 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1296   0.08997   0.08657  -0.0608   0.9745   0.0681
  -9.000  -0.2564   0.09894   0.09545  -0.0508   0.9879   0.0663
  -8.750  -0.2289   0.09535   0.09184  -0.0528   0.9846   0.0674
  -8.500  -0.2052   0.09184   0.08831  -0.0566   0.9799   0.0691
  -8.250  -0.1850   0.08810   0.08456  -0.0619   0.9731   0.0718
  -8.000  -0.1831   0.08146   0.07790  -0.0811   0.9575   0.0757
  -7.750  -0.1538   0.07849   0.07492  -0.0788   0.9567   0.0767
  -7.500  -0.1263   0.07551   0.07191  -0.0808   0.9523   0.0782
  -7.250  -0.1032   0.07222   0.06861  -0.0852   0.9442   0.0807
  -7.000  -0.0876   0.06426   0.06047  -0.1065   0.9278   0.0872
  -6.750  -0.0608   0.06201   0.05824  -0.1053   0.9242   0.0883
  -6.500  -0.0413   0.06010   0.05632  -0.1049   0.9147   0.0899
  -6.250  -0.0279   0.05471   0.05045  -0.1193   0.8980   0.0992
  -6.000  -0.0072   0.05144   0.04729  -0.1183   0.8921   0.1003
  -5.750   0.0104   0.04982   0.04570  -0.1169   0.8834   0.1015
  -5.500   0.0305   0.04828   0.04413  -0.1164   0.8756   0.1038
  -5.250   0.0447   0.04436   0.03980  -0.1214   0.8643   0.1140
  -5.000   0.0657   0.04252   0.03799  -0.1207   0.8575   0.1154
  -4.750   0.0839   0.04116   0.03663  -0.1198   0.8491   0.1177
  -4.500   0.1047   0.03850   0.03354  -0.1222   0.8409   0.1290
  -4.250   0.1241   0.03684   0.03194  -0.1213   0.8333   0.1307
  -4.000   0.1454   0.03559   0.03066  -0.1207   0.8258   0.1343
  -3.750   0.1678   0.03366   0.02843  -0.1215   0.8189   0.1459
  -3.500   0.1882   0.03239   0.02719  -0.1206   0.8107   0.1491
  -3.250   0.2134   0.03093   0.02537  -0.1212   0.8045   0.1618
  -3.000   0.2371   0.02299   0.01607  -0.1204   0.7971   0.0977
  -2.750   0.2622   0.02141   0.01426  -0.1199   0.7902   0.0961
  -2.500   0.2878   0.02006   0.01265  -0.1193   0.7837   0.0940
  -2.250   0.3126   0.01895   0.01130  -0.1185   0.7758   0.0923
  -2.000   0.3411   0.01806   0.01015  -0.1182   0.7699   0.0917
  -1.750   0.3654   0.01747   0.00944  -0.1172   0.7615   0.0918
  -1.500   0.3930   0.01695   0.00881  -0.1169   0.7546   0.0930
  -1.250   0.4191   0.01656   0.00835  -0.1162   0.7472   0.0945
  -1.000   0.4455   0.01614   0.00785  -0.1156   0.7394   0.0956
  -0.750   0.4733   0.01576   0.00739  -0.1153   0.7329   0.0965
  -0.500   0.4981   0.01546   0.00708  -0.1144   0.7242   0.0977
  -0.250   0.5265   0.01519   0.00672  -0.1141   0.7178   0.0990
   0.000   0.5498   0.01480   0.00643  -0.1131   0.7089   0.1017
   0.250   0.5770   0.01457   0.00619  -0.1127   0.7018   0.1059
   0.500   0.6016   0.01445   0.00610  -0.1118   0.6933   0.1105
   0.750   0.6280   0.01424   0.00589  -0.1112   0.6856   0.1161
   1.000   0.6533   0.01413   0.00582  -0.1105   0.6774   0.1260
   1.250   0.6789   0.01389   0.00575  -0.1098   0.6692   0.1619
   1.500   0.6963   0.01274   0.00585  -0.1080   0.6617   0.5601
   1.750   0.7676   0.01195   0.00572  -0.1166   0.6518   1.0000
   2.000   0.7919   0.01206   0.00573  -0.1156   0.6430   1.0000
   2.250   0.8170   0.01214   0.00570  -0.1148   0.6343   1.0000
   2.500   0.8408   0.01226   0.00576  -0.1138   0.6250   1.0000
   2.750   0.8663   0.01234   0.00573  -0.1131   0.6164   1.0000
   3.000   0.8896   0.01248   0.00584  -0.1120   0.6065   1.0000
   3.250   0.9157   0.01259   0.00582  -0.1114   0.5983   1.0000
   3.500   0.9382   0.01274   0.00597  -0.1102   0.5880   1.0000
   3.750   0.9635   0.01289   0.00603  -0.1095   0.5795   1.0000
   4.000   0.9866   0.01306   0.00618  -0.1085   0.5696   1.0000
   4.250   1.0109   0.01324   0.00631  -0.1076   0.5603   1.0000
   4.500   1.0349   0.01343   0.00644  -0.1067   0.5509   1.0000
   4.750   1.0582   0.01365   0.00665  -0.1058   0.5413   1.0000
   5.000   1.0832   0.01387   0.00678  -0.1051   0.5324   1.0000
   5.250   1.1049   0.01409   0.00705  -0.1038   0.5219   1.0000
   5.500   1.1291   0.01435   0.00723  -0.1030   0.5128   1.0000
   5.750   1.1512   0.01459   0.00749  -0.1019   0.5028   1.0000
   6.000   1.1741   0.01488   0.00777  -0.1009   0.4932   1.0000
   6.250   1.1971   0.01515   0.00799  -0.0999   0.4835   1.0000
   6.500   1.2178   0.01542   0.00831  -0.0986   0.4727   1.0000
   6.750   1.2400   0.01572   0.00856  -0.0975   0.4625   1.0000
   7.000   1.2601   0.01599   0.00882  -0.0960   0.4511   1.0000
   7.250   1.2790   0.01628   0.00914  -0.0943   0.4392   1.0000
   7.500   1.2988   0.01660   0.00943  -0.0929   0.4280   1.0000
   7.750   1.3181   0.01692   0.00974  -0.0913   0.4170   1.0000
   8.000   1.3352   0.01725   0.01012  -0.0894   0.4052   1.0000
   8.250   1.3527   0.01762   0.01048  -0.0876   0.3941   1.0000
   8.500   1.3695   0.01801   0.01082  -0.0857   0.3826   1.0000
   8.750   1.3827   0.01836   0.01123  -0.0831   0.3699   1.0000
   9.000   1.3960   0.01876   0.01166  -0.0807   0.3580   1.0000
   9.250   1.4068   0.01920   0.01208  -0.0778   0.3465   1.0000
   9.500   1.4158   0.01969   0.01253  -0.0746   0.3348   1.0000
   9.750   1.4250   0.02017   0.01309  -0.0716   0.3229   1.0000
  10.000   1.4346   0.02074   0.01369  -0.0689   0.3118   1.0000
  10.250   1.4428   0.02141   0.01434  -0.0660   0.3006   1.0000
  10.500   1.4505   0.02212   0.01508  -0.0633   0.2889   1.0000
  10.750   1.4578   0.02290   0.01592  -0.0606   0.2765   1.0000
  11.000   1.4636   0.02382   0.01686  -0.0580   0.2635   1.0000
  11.250   1.4675   0.02490   0.01795  -0.0553   0.2490   1.0000
  11.500   1.4695   0.02618   0.01924  -0.0527   0.2325   1.0000
  11.750   1.4677   0.02782   0.02084  -0.0500   0.2125   1.0000
  12.000   1.4625   0.02987   0.02281  -0.0474   0.1859   1.0000
  12.250   1.4500   0.03268   0.02543  -0.0447   0.1527   1.0000
  12.500   1.4347   0.03599   0.02853  -0.0423   0.1219   1.0000
  12.750   1.4211   0.03938   0.03180  -0.0404   0.1044   1.0000
  13.000   1.4107   0.04268   0.03505  -0.0388   0.0943   1.0000
  13.250   1.4016   0.04600   0.03837  -0.0377   0.0878   1.0000
  13.500   1.3943   0.04930   0.04170  -0.0367   0.0823   1.0000
  13.750   1.3846   0.05296   0.04536  -0.0360   0.0784   1.0000
  14.000   1.3819   0.05599   0.04849  -0.0355   0.0742   1.0000
  14.250   1.3758   0.05948   0.05199  -0.0351   0.0711   1.0000
  14.500   1.3707   0.06285   0.05536  -0.0346   0.0681   1.0000
  14.750   1.3709   0.06576   0.05837  -0.0344   0.0651   1.0000
  15.000   1.3703   0.06878   0.06144  -0.0343   0.0625   1.0000
  15.250   1.3714   0.07128   0.06382  -0.0335   0.0599   1.0000
  15.500   1.3738   0.07410   0.06681  -0.0336   0.0578   1.0000
  15.750   1.3769   0.07676   0.06955  -0.0335   0.0556   1.0000
  16.000   1.3815   0.07915   0.07194  -0.0333   0.0537   1.0000
  16.250   1.3924   0.08039   0.07308  -0.0321   0.0515   1.0000
  16.500   1.3947   0.08333   0.07620  -0.0324   0.0500   1.0000
  16.750   1.3985   0.08601   0.07899  -0.0325   0.0483   1.0000
  17.000   1.4041   0.08839   0.08142  -0.0326   0.0469   1.0000
  17.250   1.4141   0.09002   0.08300  -0.0321   0.0454   1.0000
  17.500   1.4246   0.09166   0.08469  -0.0314   0.0440   1.0000
  17.750   1.4247   0.09501   0.08824  -0.0321   0.0431   1.0000
  18.000   1.4258   0.09821   0.09159  -0.0327   0.0420   1.0000
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