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GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 478 AIRFOIL (goe478-il)
Reynolds number: 200,000
Max Cl/Cd: 73.45 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe478-il-200000.txt
Download as CSV file: xf-goe478-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 478 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2103   0.08981   0.08617  -0.0658   0.9724   0.0796
  -8.250  -0.1884   0.08639   0.08275  -0.0697   0.9684   0.0819
  -8.000  -0.2169   0.07672   0.07305  -0.0917   0.9491   0.0870
  -7.750  -0.1843   0.07491   0.07127  -0.0883   0.9485   0.0877
  -7.500  -0.1551   0.07261   0.06896  -0.0885   0.9461   0.0890
  -7.250  -0.1299   0.06924   0.06557  -0.0929   0.9428   0.0911
  -7.000  -0.1407   0.05931   0.05535  -0.1107   0.9278   0.0982
  -6.750  -0.1088   0.05714   0.05324  -0.1116   0.9260   0.0993
  -6.500  -0.0926   0.05559   0.05170  -0.1107   0.9183   0.1010
  -6.250  -0.1568   0.03422   0.02855  -0.1148   0.9004   0.0695
  -6.000  -0.1332   0.03170   0.02588  -0.1150   0.8957   0.0679
  -5.750  -0.1087   0.02865   0.02249  -0.1156   0.8920   0.0667
  -5.500  -0.0986   0.02661   0.02011  -0.1129   0.8840   0.0659
  -5.250  -0.0766   0.02477   0.01792  -0.1121   0.8786   0.0664
  -5.000  -0.0475   0.02309   0.01588  -0.1124   0.8747   0.0673
  -4.750  -0.0268   0.02198   0.01450  -0.1109   0.8687   0.0679
  -4.500  -0.0045   0.02103   0.01332  -0.1097   0.8630   0.0684
  -4.250   0.0241   0.01998   0.01207  -0.1097   0.8588   0.0694
  -4.000   0.0566   0.01900   0.01108  -0.1104   0.8555   0.0710
  -3.750   0.0761   0.01862   0.01071  -0.1087   0.8490   0.0726
  -3.500   0.1017   0.01817   0.01019  -0.1081   0.8437   0.0753
  -3.250   0.1319   0.01752   0.00946  -0.1082   0.8395   0.0782
  -3.000   0.1606   0.01702   0.00901  -0.1081   0.8349   0.0814
  -2.750   0.1813   0.01673   0.00872  -0.1065   0.8278   0.0851
  -2.500   0.2091   0.01622   0.00824  -0.1061   0.8226   0.0901
  -2.250   0.2411   0.01578   0.00777  -0.1065   0.8185   0.0988
  -2.000   0.2597   0.01559   0.00764  -0.1046   0.8107   0.1089
  -1.750   0.2853   0.01497   0.00718  -0.1038   0.8045   0.1301
  -1.500   0.3157   0.01461   0.00692  -0.1040   0.7992   0.1650
  -1.250   0.3361   0.01454   0.00694  -0.1023   0.7906   0.1890
  -1.000   0.3655   0.01429   0.00672  -0.1023   0.7844   0.2145
  -0.750   0.3898   0.01410   0.00658  -0.1013   0.7768   0.2401
  -0.500   0.4141   0.01376   0.00638  -0.1004   0.7685   0.2720
  -0.250   0.4400   0.01330   0.00618  -0.0998   0.7612   0.3327
   0.000   0.4499   0.01231   0.00622  -0.0960   0.7512   0.5973
   0.250   0.5690   0.01162   0.00621  -0.1126   0.7449   0.9747
   0.500   0.6396   0.01156   0.00603  -0.1212   0.7328   1.0000
   0.750   0.6615   0.01157   0.00591  -0.1198   0.7222   1.0000
   1.000   0.6824   0.01157   0.00580  -0.1181   0.7102   1.0000
   1.250   0.7010   0.01161   0.00578  -0.1161   0.6973   1.0000
   1.500   0.7230   0.01164   0.00569  -0.1146   0.6855   1.0000
   1.750   0.7433   0.01167   0.00562  -0.1129   0.6725   1.0000
   2.000   0.7619   0.01173   0.00564  -0.1108   0.6585   1.0000
   2.250   0.7823   0.01179   0.00562  -0.1091   0.6457   1.0000
   2.500   0.8041   0.01185   0.00556  -0.1076   0.6339   1.0000
   2.750   0.8239   0.01193   0.00558  -0.1059   0.6208   1.0000
   3.000   0.8440   0.01204   0.00562  -0.1041   0.6081   1.0000
   3.250   0.8647   0.01215   0.00563  -0.1025   0.5952   1.0000
   3.500   0.8858   0.01228   0.00563  -0.1009   0.5825   1.0000
   3.750   0.9064   0.01247   0.00571  -0.0993   0.5702   1.0000
   4.000   0.9272   0.01269   0.00587  -0.0977   0.5592   1.0000
   4.250   0.9505   0.01296   0.00600  -0.0967   0.5494   1.0000
   4.500   0.9707   0.01322   0.00623  -0.0951   0.5389   1.0000
   4.750   0.9936   0.01353   0.00644  -0.0940   0.5297   1.0000
   5.000   1.0144   0.01381   0.00669  -0.0926   0.5201   1.0000
   5.250   1.0369   0.01413   0.00695  -0.0915   0.5113   1.0000
   5.500   1.0575   0.01441   0.00722  -0.0900   0.5024   1.0000
   5.750   1.0804   0.01475   0.00751  -0.0890   0.4941   1.0000
   6.000   1.0996   0.01501   0.00780  -0.0873   0.4852   1.0000
   6.250   1.1223   0.01535   0.00807  -0.0862   0.4768   1.0000
   6.500   1.1396   0.01558   0.00836  -0.0841   0.4673   1.0000
   6.750   1.1594   0.01587   0.00861  -0.0825   0.4575   1.0000
   7.000   1.1750   0.01607   0.00883  -0.0801   0.4463   1.0000
   7.250   1.1901   0.01629   0.00907  -0.0776   0.4348   1.0000
   7.500   1.2062   0.01654   0.00927  -0.0753   0.4235   1.0000
   7.750   1.2185   0.01674   0.00953  -0.0724   0.4114   1.0000
   8.000   1.2316   0.01700   0.00981  -0.0696   0.3996   1.0000
   8.250   1.2428   0.01728   0.01006  -0.0665   0.3878   1.0000
   8.500   1.2506   0.01756   0.01036  -0.0627   0.3744   1.0000
   8.750   1.2583   0.01791   0.01072  -0.0591   0.3596   1.0000
   9.000   1.2656   0.01833   0.01113  -0.0556   0.3434   1.0000
   9.250   1.2720   0.01886   0.01162  -0.0521   0.3257   1.0000
   9.500   1.2765   0.01954   0.01221  -0.0486   0.3065   1.0000
   9.750   1.2811   0.02033   0.01294  -0.0452   0.2860   1.0000
  10.000   1.2848   0.02127   0.01380  -0.0420   0.2666   1.0000
  10.250   1.2884   0.02233   0.01476  -0.0390   0.2492   1.0000
  10.500   1.2922   0.02348   0.01583  -0.0362   0.2336   1.0000
  10.750   1.2966   0.02469   0.01697  -0.0336   0.2199   1.0000
  11.000   1.3006   0.02598   0.01821  -0.0312   0.2078   1.0000
  11.250   1.3046   0.02735   0.01951  -0.0289   0.1963   1.0000
  11.500   1.3107   0.02864   0.02082  -0.0269   0.1851   1.0000
  11.750   1.3151   0.03010   0.02225  -0.0250   0.1750   1.0000
  12.000   1.3175   0.03174   0.02382  -0.0230   0.1658   1.0000
  12.250   1.3230   0.03323   0.02537  -0.0214   0.1562   1.0000
  12.500   1.3255   0.03500   0.02709  -0.0197   0.1482   1.0000
  12.750   1.3296   0.03668   0.02879  -0.0182   0.1406   1.0000
  13.000   1.3331   0.03848   0.03057  -0.0167   0.1341   1.0000
  13.250   1.3378   0.04022   0.03234  -0.0155   0.1280   1.0000
  13.500   1.3416   0.04207   0.03413  -0.0141   0.1230   1.0000
  13.750   1.3476   0.04379   0.03595  -0.0131   0.1181   1.0000
  14.000   1.3530   0.04557   0.03772  -0.0121   0.1143   1.0000
  14.250   1.3610   0.04719   0.03930  -0.0110   0.1107   1.0000
  14.500   1.3680   0.04892   0.04114  -0.0102   0.1076   1.0000
  14.750   1.3751   0.05065   0.04292  -0.0094   0.1047   1.0000
  15.000   1.3836   0.05226   0.04450  -0.0086   0.1020   1.0000
  15.250   1.3955   0.05364   0.04588  -0.0077   0.0995   1.0000
  15.500   1.4009   0.05563   0.04802  -0.0071   0.0974   1.0000
  15.750   1.4076   0.05750   0.04999  -0.0066   0.0952   1.0000
  16.000   1.4152   0.05929   0.05182  -0.0061   0.0932   1.0000
  16.250   1.4266   0.06072   0.05321  -0.0055   0.0911   1.0000
  16.500   1.4381   0.06227   0.05479  -0.0049   0.0891   1.0000
  16.750   1.4387   0.06485   0.05757  -0.0046   0.0876   1.0000
  17.000   1.4408   0.06733   0.06019  -0.0045   0.0859   1.0000
  17.250   1.4444   0.06966   0.06260  -0.0044   0.0841   1.0000
  17.500   1.4519   0.07153   0.06447  -0.0043   0.0823   1.0000
  17.750   1.4686   0.07253   0.06539  -0.0036   0.0801   1.0000
  18.000   1.4618   0.07613   0.06923  -0.0041   0.0790   1.0000
  18.250   1.4574   0.07959   0.07289  -0.0046   0.0778   1.0000
  18.500   1.4538   0.08301   0.07647  -0.0052   0.0763   1.0000
  18.750   1.4539   0.08598   0.07953  -0.0058   0.0749   1.0000
  19.000   1.4596   0.08818   0.08176  -0.0061   0.0734   1.0000
  19.250   1.4778   0.08883   0.08230  -0.0054   0.0714   1.0000
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