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GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 484 AIRFOIL (goe484-il)
Reynolds number: 200,000
Max Cl/Cd: 93.35 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe484-il-200000.txt
Download as CSV file: xf-goe484-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 484 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3726   0.09934   0.09589  -0.0228   1.0000   0.0403
  -7.500  -0.3884   0.09884   0.09546  -0.0204   1.0000   0.0409
  -7.250  -0.4061   0.09850   0.09519  -0.0181   1.0000   0.0413
  -7.000  -0.4145   0.09729   0.09403  -0.0202   1.0000   0.0416
  -6.750  -0.4138   0.09505   0.09181  -0.0241   1.0000   0.0419
  -6.500  -0.4037   0.08953   0.08630  -0.0261   0.9981   0.0424
  -6.250  -0.3882   0.08576   0.08253  -0.0241   0.9957   0.0435
  -6.000  -0.3655   0.08230   0.07905  -0.0269   0.9921   0.0452
  -5.750  -0.3402   0.07862   0.07534  -0.0327   0.9876   0.0481
  -5.500  -0.2699   0.07158   0.06805  -0.0607   0.9811   0.0526
  -5.250  -0.2655   0.06760   0.06414  -0.0570   0.9775   0.0536
  -5.000  -0.2462   0.06493   0.06147  -0.0571   0.9742   0.0552
  -4.750  -0.2132   0.06159   0.05809  -0.0624   0.9716   0.0582
  -4.500  -0.1558   0.05492   0.05110  -0.0795   0.9656   0.0653
  -4.250  -0.1386   0.05267   0.04892  -0.0785   0.9619   0.0670
  -4.000  -0.1051   0.04996   0.04616  -0.0823   0.9591   0.0704
  -3.750  -0.0451   0.04439   0.04020  -0.0950   0.9568   0.0791
  -3.500  -0.0280   0.04251   0.03837  -0.0943   0.9503   0.0811
  -3.250   0.0096   0.04011   0.03584  -0.0983   0.9470   0.0876
  -3.000   0.0538   0.03668   0.03219  -0.1042   0.9448   0.0954
  -2.750   0.0975   0.03427   0.02940  -0.1091   0.9415   0.1075
  -2.500   0.1215   0.03231   0.02749  -0.1094   0.9353   0.1102
  -2.250   0.1647   0.03025   0.02509  -0.1134   0.9322   0.1227
  -2.000   0.2180   0.02472   0.01848  -0.1173   0.9309   0.0777
  -1.750   0.2599   0.02114   0.01429  -0.1199   0.9296   0.0647
  -1.500   0.2868   0.02011   0.01306  -0.1196   0.9229   0.0645
  -1.250   0.3235   0.01852   0.01127  -0.1212   0.9192   0.0632
  -1.000   0.3639   0.01735   0.00995  -0.1234   0.9167   0.0625
  -0.750   0.4065   0.01639   0.00893  -0.1260   0.9148   0.0628
  -0.500   0.4321   0.01589   0.00841  -0.1253   0.9065   0.0635
  -0.250   0.4721   0.01513   0.00768  -0.1274   0.9034   0.0654
   0.000   0.5149   0.01447   0.00712  -0.1301   0.9011   0.0717
   0.250   0.5443   0.01413   0.00682  -0.1301   0.8934   0.0789
   0.500   0.5824   0.01351   0.00643  -0.1318   0.8888   0.1184
   0.750   0.6226   0.01269   0.00612  -0.1341   0.8856   0.2769
   1.000   0.6562   0.01120   0.00614  -0.1351   0.8778   1.0000
   1.250   0.6936   0.01095   0.00581  -0.1365   0.8722   1.0000
   1.500   0.7233   0.01080   0.00559  -0.1363   0.8614   1.0000
   1.750   0.7558   0.01053   0.00527  -0.1365   0.8499   1.0000
   2.000   0.7862   0.01021   0.00488  -0.1360   0.8333   1.0000
   2.250   0.8158   0.00994   0.00452  -0.1354   0.8133   1.0000
   2.500   0.8416   0.00984   0.00436  -0.1342   0.7908   1.0000
   2.750   0.8677   0.00979   0.00422  -0.1332   0.7666   1.0000
   3.000   0.8916   0.00980   0.00416  -0.1318   0.7371   1.0000
   3.250   0.9153   0.00988   0.00413  -0.1304   0.7037   1.0000
   3.500   0.9391   0.01006   0.00417  -0.1291   0.6683   1.0000
   3.750   0.9603   0.01044   0.00427  -0.1272   0.6210   1.0000
   4.000   0.9771   0.01105   0.00451  -0.1245   0.5563   1.0000
   4.250   0.9825   0.01221   0.00486  -0.1199   0.3919   1.0000
   4.500   0.9743   0.01520   0.00614  -0.1141   0.1134   1.0000
   4.750   0.9913   0.01624   0.00699  -0.1121   0.0843   1.0000
   5.000   1.0103   0.01704   0.00777  -0.1104   0.0766   1.0000
   5.250   1.0297   0.01775   0.00854  -0.1088   0.0720   1.0000
   5.500   1.0485   0.01850   0.00932  -0.1071   0.0680   1.0000
   5.750   1.0654   0.01946   0.01027  -0.1051   0.0651   1.0000
   6.000   1.0799   0.02091   0.01171  -0.1028   0.0625   1.0000
   6.250   1.1003   0.02177   0.01262  -0.1014   0.0605   1.0000
   6.500   1.1213   0.02272   0.01362  -0.1001   0.0580   1.0000
   6.750   1.1438   0.02390   0.01482  -0.0991   0.0560   1.0000
   7.000   1.1673   0.02515   0.01609  -0.0984   0.0535   1.0000
   7.250   1.1990   0.02801   0.01887  -0.0995   0.0502   1.0000
   7.500   1.2256   0.02965   0.02068  -0.0990   0.0490   1.0000
   7.750   1.2492   0.03092   0.02215  -0.0980   0.0474   1.0000
   8.000   1.2722   0.03239   0.02384  -0.0970   0.0452   1.0000
   8.250   1.2961   0.03451   0.02618  -0.0962   0.0439   1.0000
   8.500   1.3184   0.03702   0.02896  -0.0951   0.0432   1.0000
   8.750   1.3388   0.03933   0.03143  -0.0940   0.0418   1.0000
   9.000   1.3582   0.04274   0.03490  -0.0935   0.0399   1.0000
   9.250   1.3733   0.04631   0.03883  -0.0916   0.0398   1.0000
  13.250   1.0747   0.14760   0.14427  -0.0896   0.0603   1.0000
  13.500   1.0622   0.15709   0.15372  -0.0966   0.0579   1.0000
  13.750   0.9223   0.15482   0.15191  -0.0849   0.0621   1.0000
  14.000   0.9025   0.16292   0.15998  -0.0918   0.0617   1.0000
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