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GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 477 AIRFOIL (goe477-il)
Reynolds number: 200,000
Max Cl/Cd: 80.51 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe477-il-200000.txt
Download as CSV file: xf-goe477-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 477 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2758   0.09813   0.09484  -0.0574   0.9818   0.0526
  -8.750  -0.2691   0.09420   0.09092  -0.0653   0.9749   0.0530
  -8.500  -0.2589   0.08796   0.08470  -0.0716   0.9714   0.0534
  -8.250  -0.2384   0.08403   0.08074  -0.0695   0.9709   0.0545
  -8.000  -0.2240   0.08126   0.07796  -0.0698   0.9668   0.0557
  -7.750  -0.2098   0.07810   0.07479  -0.0726   0.9623   0.0573
  -7.500  -0.1934   0.07412   0.07080  -0.0784   0.9585   0.0596
  -7.250  -0.1811   0.06791   0.06445  -0.0961   0.9482   0.0644
  -7.000  -0.1683   0.06069   0.05710  -0.1034   0.9439   0.0656
  -6.750  -0.1482   0.05881   0.05529  -0.1014   0.9426   0.0673
  -6.500  -0.1361   0.05670   0.05317  -0.1013   0.9378   0.0691
  -6.250  -0.1225   0.05382   0.05021  -0.1032   0.9325   0.0721
  -6.000  -0.1031   0.04627   0.04208  -0.1123   0.9273   0.0793
  -5.750  -0.0902   0.04487   0.04082  -0.1104   0.9232   0.0811
  -5.500  -0.0898   0.03520   0.03018  -0.1108   0.9155   0.0661
  -5.250  -0.0656   0.03154   0.02629  -0.1114   0.9130   0.0619
  -5.000  -0.0495   0.02858   0.02279  -0.1101   0.9088   0.0632
  -4.750  -0.0374   0.02689   0.02058  -0.1076   0.9032   0.0653
  -4.500  -0.0138   0.02446   0.01794  -0.1077   0.9002   0.0680
  -4.250   0.0166   0.02370   0.01711  -0.1084   0.8980   0.0726
  -4.000   0.0481   0.02249   0.01548  -0.1088   0.8961   0.0767
  -3.750   0.0577   0.02182   0.01457  -0.1057   0.8895   0.0794
  -3.500   0.0857   0.02089   0.01362  -0.1059   0.8859   0.0840
  -3.250   0.1209   0.02006   0.01261  -0.1069   0.8828   0.0889
  -3.000   0.1527   0.01960   0.01193  -0.1071   0.8790   0.0925
  -2.750   0.1719   0.01874   0.01106  -0.1056   0.8723   0.0959
  -2.500   0.2037   0.01820   0.01051  -0.1061   0.8686   0.1010
  -2.250   0.2375   0.01762   0.00984  -0.1067   0.8657   0.1051
  -2.000   0.2562   0.01741   0.00961  -0.1049   0.8584   0.1084
  -1.750   0.2853   0.01689   0.00915  -0.1048   0.8539   0.1144
  -1.500   0.3193   0.01634   0.00854  -0.1052   0.8499   0.1208
  -1.250   0.3403   0.01595   0.00823  -0.1036   0.8401   0.1278
  -1.000   0.3736   0.01527   0.00757  -0.1036   0.8341   0.1431
  -0.750   0.3947   0.01490   0.00737  -0.1020   0.8244   0.1755
  -0.500   0.4196   0.01384   0.00707  -0.1012   0.8198   0.3771
  -0.250   0.5067   0.01206   0.00677  -0.1127   0.8161   1.0000
   0.000   0.5295   0.01209   0.00668  -0.1114   0.8088   1.0000
   0.250   0.5571   0.01200   0.00646  -0.1108   0.8037   1.0000
   0.500   0.5773   0.01208   0.00649  -0.1091   0.7949   1.0000
   0.750   0.6052   0.01196   0.00625  -0.1086   0.7896   1.0000
   1.000   0.6258   0.01201   0.00628  -0.1069   0.7805   1.0000
   1.250   0.6538   0.01183   0.00600  -0.1064   0.7743   1.0000
   1.500   0.6749   0.01180   0.00596  -0.1048   0.7639   1.0000
   1.750   0.7000   0.01165   0.00576  -0.1037   0.7553   1.0000
   2.000   0.7249   0.01147   0.00554  -0.1027   0.7454   1.0000
   2.250   0.7474   0.01136   0.00543  -0.1013   0.7336   1.0000
   2.500   0.7708   0.01120   0.00526  -0.1000   0.7205   1.0000
   2.750   0.7942   0.01104   0.00509  -0.0987   0.7045   1.0000
   3.000   0.8182   0.01085   0.00485  -0.0974   0.6843   1.0000
   3.250   0.8412   0.01072   0.00462  -0.0959   0.6552   1.0000
   3.500   0.8631   0.01072   0.00440  -0.0942   0.6118   1.0000
   3.750   0.8808   0.01106   0.00438  -0.0918   0.5518   1.0000
   4.000   0.8943   0.01167   0.00459  -0.0890   0.4900   1.0000
   4.250   0.9083   0.01236   0.00495  -0.0864   0.4489   1.0000
   4.500   0.9246   0.01300   0.00537  -0.0843   0.4202   1.0000
   4.750   0.9424   0.01360   0.00579  -0.0825   0.3982   1.0000
   5.000   0.9618   0.01412   0.00621  -0.0811   0.3794   1.0000
   5.250   0.9817   0.01463   0.00662  -0.0797   0.3636   1.0000
   5.500   1.0021   0.01513   0.00704  -0.0785   0.3506   1.0000
   5.750   1.0231   0.01560   0.00745  -0.0773   0.3395   1.0000
   6.000   1.0451   0.01602   0.00788  -0.0764   0.3300   1.0000
   6.250   1.0669   0.01653   0.00831  -0.0754   0.3216   1.0000
   6.500   1.0875   0.01689   0.00871  -0.0743   0.3119   1.0000
   6.750   1.1077   0.01729   0.00911  -0.0730   0.3024   1.0000
   7.000   1.1276   0.01774   0.00950  -0.0718   0.2936   1.0000
   7.250   1.1473   0.01807   0.00992  -0.0705   0.2851   1.0000
   7.500   1.1662   0.01852   0.01034  -0.0692   0.2767   1.0000
   7.750   1.1833   0.01882   0.01074  -0.0674   0.2673   1.0000
   8.000   1.1999   0.01921   0.01117  -0.0657   0.2588   1.0000
   8.250   1.2142   0.01960   0.01158  -0.0635   0.2499   1.0000
   8.500   1.2262   0.01993   0.01201  -0.0610   0.2378   1.0000
   8.750   1.2366   0.02035   0.01247  -0.0584   0.2221   1.0000
   9.000   1.2457   0.02087   0.01297  -0.0557   0.1937   1.0000
   9.250   1.2392   0.02285   0.01419  -0.0516   0.0819   1.0000
   9.500   1.2366   0.02505   0.01618  -0.0481   0.0571   1.0000
   9.750   1.2449   0.02635   0.01759  -0.0459   0.0511   1.0000
  10.000   1.2488   0.02794   0.01930  -0.0434   0.0472   1.0000
  10.250   1.2488   0.02979   0.02128  -0.0407   0.0448   1.0000
  10.500   1.2542   0.03129   0.02291  -0.0386   0.0430   1.0000
  10.750   1.2567   0.03303   0.02476  -0.0365   0.0412   1.0000
  11.000   1.2576   0.03497   0.02677  -0.0345   0.0392   1.0000
  11.250   1.2556   0.03722   0.02907  -0.0325   0.0378   1.0000
  11.500   1.2517   0.03979   0.03168  -0.0304   0.0367   1.0000
  11.750   1.2523   0.04217   0.03410  -0.0286   0.0358   1.0000
  12.000   1.2591   0.04399   0.03605  -0.0273   0.0351   1.0000
  12.250   1.2668   0.04584   0.03798  -0.0260   0.0343   1.0000
  12.500   1.2748   0.04772   0.03993  -0.0248   0.0329   1.0000
  12.750   1.2836   0.04957   0.04184  -0.0238   0.0318   1.0000
  13.000   1.2917   0.05155   0.04387  -0.0228   0.0306   1.0000
  13.250   1.3069   0.05335   0.04568  -0.0218   0.0297   1.0000
  13.500   1.3641   0.05554   0.04783  -0.0218   0.0285   1.0000
  13.750   1.3663   0.05785   0.05034  -0.0205   0.0283   1.0000
  14.000   1.3631   0.06030   0.05302  -0.0193   0.0279   1.0000
  14.250   1.3611   0.06300   0.05596  -0.0183   0.0274   1.0000
  14.500   1.3623   0.06603   0.05920  -0.0175   0.0272   1.0000
  14.750   1.3587   0.06926   0.06265  -0.0169   0.0268   1.0000
  15.000   1.3548   0.07282   0.06644  -0.0165   0.0267   1.0000
  15.250   1.3484   0.07686   0.07071  -0.0163   0.0267   1.0000
  15.500   1.3388   0.08124   0.07532  -0.0165   0.0267   1.0000
  15.750   1.3288   0.08596   0.08028  -0.0171   0.0269   1.0000
  16.000   1.3159   0.09099   0.08553  -0.0182   0.0270   1.0000
  16.250   1.3015   0.09651   0.09126  -0.0197   0.0272   1.0000
  16.500   1.2857   0.10247   0.09743  -0.0219   0.0274   1.0000
  16.750   1.2715   0.10866   0.10380  -0.0243   0.0278   1.0000
  17.000   1.2822   0.11274   0.10797  -0.0242   0.0289   1.0000
  17.250   1.2607   0.11877   0.11423  -0.0281   0.0292   1.0000
  17.500   1.2227   0.12863   0.12440  -0.0356   0.0298   1.0000
  17.750   1.1623   0.14575   0.14193  -0.0486   0.0312   1.0000
  18.000   1.1140   0.16295   0.15935  -0.0608   0.0327   1.0000
  18.250   1.0829   0.17722   0.17370  -0.0697   0.0347   1.0000
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