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GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 63 AIRFOIL (goe63-il)
Reynolds number: 50,000
Max Cl/Cd: 41.25 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe63-il-50000-n5.txt
Download as CSV file: xf-goe63-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 63 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2338   0.11801   0.11119  -0.0305   1.0000   0.0696
  -8.500  -0.2414   0.11807   0.11141  -0.0308   1.0000   0.0699
  -8.250  -0.2531   0.11832   0.11185  -0.0300   1.0000   0.0700
  -8.000  -0.2301   0.11064   0.10417  -0.0281   1.0000   0.0715
  -7.750  -0.2364   0.10920   0.10288  -0.0256   1.0000   0.0724
  -7.500  -0.2530   0.10907   0.10290  -0.0217   1.0000   0.0728
  -7.250  -0.2342   0.10561   0.09945  -0.0258   0.9894   0.0746
  -7.000  -0.2111   0.10211   0.09592  -0.0315   0.9772   0.0769
  -6.750  -0.1872   0.09916   0.09295  -0.0386   0.9645   0.0793
  -6.500  -0.1577   0.09739   0.09111  -0.0499   0.9506   0.0809
  -6.250  -0.1311   0.09301   0.08671  -0.0551   0.9433   0.0818
  -6.000  -0.1148   0.08861   0.08232  -0.0545   0.9343   0.0839
  -5.750  -0.0885   0.08508   0.07876  -0.0588   0.9270   0.0876
  -5.500  -0.0621   0.08281   0.07642  -0.0655   0.9151   0.0919
  -5.250  -0.0251   0.08078   0.07425  -0.0760   0.9050   0.0938
  -5.000  -0.0103   0.07645   0.06996  -0.0748   0.8976   0.0956
  -4.750   0.0130   0.07332   0.06679  -0.0771   0.8902   0.0988
  -4.500   0.0413   0.07093   0.06432  -0.0820   0.8810   0.1036
  -4.250   0.0814   0.06862   0.06184  -0.0906   0.8735   0.1072
  -4.000   0.0964   0.06544   0.05869  -0.0899   0.8652   0.1099
  -3.750   0.1506   0.06443   0.05734  -0.1010   0.8592   0.1202
  -3.500   0.1566   0.06071   0.05377  -0.0980   0.8503   0.1226
  -3.250   0.2006   0.05932   0.05212  -0.1051   0.8440   0.1355
  -3.000   0.2123   0.05604   0.04896  -0.1033   0.8364   0.1394
  -2.750   0.2492   0.05438   0.04711  -0.1082   0.8294   0.1529
  -2.500   0.2740   0.05168   0.04441  -0.1089   0.8243   0.1616
  -2.250   0.2990   0.04999   0.04267  -0.1108   0.8155   0.1754
  -2.000   0.3346   0.04828   0.04082  -0.1144   0.8097   0.2031
  -1.750   0.3594   0.04671   0.03922  -0.1156   0.8023   0.2344
  -1.000   0.4270   0.04113   0.03374  -0.1153   0.7790   0.3496
  -0.500   0.5570   0.03839   0.02931  -0.1278   0.7599   0.1034
  -0.250   0.5915   0.03700   0.02759  -0.1285   0.7503   0.0909
   0.000   0.6234   0.03569   0.02606  -0.1289   0.7409   0.0860
   0.250   0.6566   0.03509   0.02497  -0.1291   0.7317   0.0811
   0.500   0.6869   0.03408   0.02379  -0.1293   0.7234   0.0817
   0.750   0.7142   0.03332   0.02292  -0.1292   0.7139   0.0828
   1.000   0.7448   0.03255   0.02192  -0.1291   0.7055   0.0826
   1.250   0.7720   0.03215   0.02130  -0.1285   0.6954   0.0818
   1.500   0.8024   0.03143   0.02036  -0.1281   0.6873   0.0817
   1.750   0.8274   0.03112   0.01989  -0.1273   0.6761   0.0823
   2.000   0.8572   0.03041   0.01901  -0.1266   0.6680   0.0855
   2.250   0.8807   0.03029   0.01880  -0.1255   0.6559   0.0892
   2.500   0.9065   0.03002   0.01838  -0.1244   0.6453   0.0920
   2.750   0.9337   0.02954   0.01779  -0.1233   0.6353   0.0945
   3.000   0.9568   0.02943   0.01770  -0.1223   0.6224   0.0993
   3.250   0.9825   0.02925   0.01745  -0.1213   0.6108   0.1080
   3.500   1.0102   0.02889   0.01703  -0.1205   0.5997   0.1186
   3.750   1.0338   0.02889   0.01712  -0.1196   0.5853   0.1373
   4.000   1.0569   0.02791   0.01736  -0.1190   0.5717   0.5966
   4.500   1.1018   0.02802   0.01716  -0.1155   0.5437   1.0000
   4.750   1.1259   0.02821   0.01719  -0.1144   0.5293   1.0000
   5.000   1.1496   0.02842   0.01727  -0.1133   0.5144   1.0000
   5.250   1.1720   0.02876   0.01754  -0.1121   0.4987   1.0000
   5.500   1.1941   0.02913   0.01782  -0.1110   0.4831   1.0000
   5.750   1.2159   0.02954   0.01814  -0.1098   0.4678   1.0000
   6.000   1.2375   0.03000   0.01852  -0.1086   0.4528   1.0000
   6.250   1.2588   0.03052   0.01898  -0.1074   0.4384   1.0000
   6.500   1.2798   0.03108   0.01947  -0.1063   0.4246   1.0000
   6.750   1.3009   0.03167   0.01997  -0.1051   0.4115   1.0000
   7.000   1.3223   0.03224   0.02046  -0.1040   0.3991   1.0000
   7.250   1.3417   0.03301   0.02119  -0.1027   0.3864   1.0000
   7.500   1.3599   0.03389   0.02208  -0.1014   0.3741   1.0000
   7.750   1.3790   0.03471   0.02286  -0.1002   0.3626   1.0000
   8.000   1.3992   0.03549   0.02359  -0.0991   0.3517   1.0000
   8.250   1.4144   0.03662   0.02481  -0.0976   0.3403   1.0000
   8.500   1.4325   0.03756   0.02573  -0.0963   0.3301   1.0000
   8.750   1.4490   0.03861   0.02684  -0.0950   0.3198   1.0000
   9.000   1.4631   0.03984   0.02816  -0.0934   0.3101   1.0000
   9.250   1.4816   0.04079   0.02907  -0.0923   0.3010   1.0000
   9.500   1.4905   0.04231   0.03078  -0.0903   0.2917   1.0000
   9.750   1.5097   0.04324   0.03169  -0.0892   0.2836   1.0000
  10.000   1.5139   0.04502   0.03371  -0.0869   0.2753   1.0000
  10.250   1.5294   0.04608   0.03476  -0.0855   0.2679   1.0000
  10.500   1.5309   0.04797   0.03686  -0.0830   0.2608   1.0000
  10.750   1.5391   0.04951   0.03851  -0.0812   0.2540   1.0000
  11.000   1.5499   0.05103   0.04013  -0.0796   0.2481   1.0000
  11.250   1.5471   0.05350   0.04285  -0.0775   0.2420   1.0000
  11.500   1.5595   0.05485   0.04424  -0.0762   0.2364   1.0000
  11.750   1.5581   0.05742   0.04700  -0.0745   0.2313   1.0000
  12.000   1.5507   0.06062   0.05044  -0.0730   0.2262   1.0000
  12.250   1.5595   0.06239   0.05229  -0.0718   0.2215   1.0000
  12.500   1.5629   0.06486   0.05492  -0.0708   0.2176   1.0000
  12.750   1.5353   0.07066   0.06106  -0.0701   0.2137   1.0000
  13.000   1.5160   0.07593   0.06655  -0.0699   0.2099   1.0000
  13.250   1.5235   0.07800   0.06871  -0.0691   0.2062   1.0000
  13.500   1.5168   0.08198   0.07282  -0.0690   0.2030   1.0000
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