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GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 650 AIRFOIL (goe650-il)
Reynolds number: 100,000
Max Cl/Cd: 56.04 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe650-il-100000.txt
Download as CSV file: xf-goe650-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 650 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3754   0.10285   0.09799  -0.0236   1.0000   0.1645
  -8.000  -0.6126   0.06355   0.05874  -0.0499   1.0000   0.1026
  -7.750  -0.6428   0.04994   0.04450  -0.0593   1.0000   0.1020
  -7.500  -0.6445   0.04147   0.03514  -0.0638   1.0000   0.1037
  -7.250  -0.6279   0.04125   0.03510  -0.0622   1.0000   0.1062
  -7.000  -0.6120   0.04025   0.03406  -0.0614   1.0000   0.1096
  -6.750  -0.5980   0.03568   0.02854  -0.0632   1.0000   0.1158
  -6.500  -0.5803   0.03523   0.02831  -0.0619   1.0000   0.1196
  -6.250  -0.5564   0.03357   0.02625  -0.0627   0.9984   0.1274
  -6.000  -0.5184   0.03336   0.02611  -0.0653   0.9927   0.1373
  -5.750  -0.4839   0.03260   0.02518  -0.0675   0.9864   0.1492
  -5.500  -0.4472   0.03203   0.02438  -0.0700   0.9807   0.1620
  -5.250  -0.4159   0.03176   0.02388  -0.0712   0.9742   0.1734
  -5.000  -0.3784   0.03190   0.02418  -0.0734   0.9693   0.1834
  -4.750  -0.3532   0.03134   0.02340  -0.0737   0.9626   0.1934
  -4.500  -0.3174   0.03162   0.02365  -0.0755   0.9571   0.2053
  -4.250  -0.2906   0.03149   0.02359  -0.0757   0.9507   0.2140
  -4.000  -0.2581   0.03103   0.02283  -0.0771   0.9446   0.2231
  -3.750  -0.2216   0.03064   0.02243  -0.0791   0.9397   0.2299
  -3.500  -0.1979   0.03024   0.02192  -0.0787   0.9320   0.2366
  -3.250  -0.1596   0.02982   0.02134  -0.0809   0.9267   0.2449
  -3.000  -0.1340   0.02964   0.02114  -0.0808   0.9193   0.2521
  -2.750  -0.1010   0.02930   0.02063  -0.0819   0.9129   0.2608
  -2.500  -0.0603   0.02926   0.02060  -0.0843   0.9079   0.2716
  -2.250  -0.0396   0.02904   0.02034  -0.0833   0.8984   0.2800
  -2.000   0.0018   0.02893   0.02011  -0.0857   0.8933   0.2934
  -1.750   0.0224   0.02893   0.02026  -0.0846   0.8840   0.3030
  -1.500   0.0605   0.02881   0.02016  -0.0864   0.8777   0.3184
  -1.250   0.0876   0.02882   0.02017  -0.0863   0.8692   0.3335
  -1.000   0.1207   0.02878   0.02019  -0.0871   0.8618   0.3518
  -0.750   0.1673   0.02863   0.02014  -0.0900   0.8577   0.3756
  -0.500   0.1820   0.02879   0.02035  -0.0879   0.8454   0.3924
  -0.250   0.2291   0.02853   0.02012  -0.0906   0.8409   0.4220
   0.000   0.2499   0.02849   0.02018  -0.0892   0.8279   0.4421
   0.250   0.3061   0.02770   0.01946  -0.0928   0.8233   0.4743
   0.500   0.3274   0.02760   0.01943  -0.0913   0.8098   0.4948
   0.750   0.3807   0.02670   0.01866  -0.0945   0.8063   0.5242
   1.000   0.3979   0.02681   0.01883  -0.0924   0.7931   0.5441
   1.250   0.4502   0.02576   0.01792  -0.0953   0.7898   0.5742
   1.500   0.4682   0.02579   0.01802  -0.0932   0.7771   0.5962
   1.750   0.5242   0.02462   0.01698  -0.0967   0.7736   0.6320
   2.000   0.5521   0.02434   0.01683  -0.0961   0.7627   0.6626
   2.250   0.6058   0.02310   0.01580  -0.0993   0.7575   0.7124
   2.750   0.7253   0.02082   0.01406  -0.1093   0.7407   1.0000
   3.000   0.7620   0.02046   0.01357  -0.1101   0.7295   1.0000
   3.250   0.8098   0.01970   0.01269  -0.1125   0.7200   1.0000
   3.500   0.8370   0.01954   0.01246  -0.1116   0.7050   1.0000
   3.750   0.8665   0.01931   0.01217  -0.1111   0.6899   1.0000
   4.000   0.8965   0.01903   0.01184  -0.1105   0.6736   1.0000
   4.250   0.9250   0.01880   0.01153  -0.1098   0.6559   1.0000
   4.500   0.9529   0.01856   0.01122  -0.1089   0.6362   1.0000
   4.750   0.9820   0.01834   0.01087  -0.1081   0.6151   1.0000
   5.000   1.0016   0.01839   0.01085  -0.1059   0.5896   1.0000
   5.250   1.0288   0.01840   0.01064  -0.1050   0.5639   1.0000
   5.500   1.0486   0.01871   0.01079  -0.1030   0.5355   1.0000
   5.750   1.0711   0.01913   0.01099  -0.1016   0.5086   1.0000
   6.000   1.0902   0.01966   0.01136  -0.0997   0.4824   1.0000
   6.250   1.1111   0.02021   0.01171  -0.0982   0.4591   1.0000
   6.500   1.1275   0.02078   0.01220  -0.0959   0.4367   1.0000
   6.750   1.1452   0.02136   0.01268  -0.0940   0.4166   1.0000
   7.000   1.1635   0.02196   0.01317  -0.0922   0.3982   1.0000
   7.250   1.1821   0.02262   0.01371  -0.0905   0.3812   1.0000
   7.500   1.2015   0.02333   0.01432  -0.0889   0.3654   1.0000
   7.750   1.2217   0.02410   0.01500  -0.0876   0.3508   1.0000
   8.000   1.2433   0.02492   0.01571  -0.0866   0.3371   1.0000
   8.250   1.2661   0.02578   0.01644  -0.0858   0.3239   1.0000
   8.500   1.2830   0.02661   0.01734  -0.0840   0.3116   1.0000
   8.750   1.3047   0.02758   0.01828  -0.0831   0.3006   1.0000
   9.000   1.3306   0.02855   0.01912  -0.0829   0.2901   1.0000
   9.250   1.3453   0.02948   0.02021  -0.0808   0.2805   1.0000
   9.500   1.3714   0.03050   0.02110  -0.0807   0.2710   1.0000
   9.750   1.3820   0.03133   0.02210  -0.0780   0.2622   1.0000
  10.000   1.4052   0.03229   0.02296  -0.0775   0.2537   1.0000
  10.250   1.4143   0.03313   0.02400  -0.0746   0.2460   1.0000
  10.500   1.4388   0.03405   0.02477  -0.0743   0.2381   1.0000
  10.750   1.4428   0.03493   0.02592  -0.0707   0.2315   1.0000
  11.000   1.4636   0.03568   0.02657  -0.0698   0.2244   1.0000
  11.250   1.4686   0.03667   0.02775  -0.0665   0.2183   1.0000
  11.500   1.4763   0.03753   0.02873  -0.0636   0.2124   1.0000
  11.750   1.4992   0.03841   0.02949  -0.0632   0.2059   1.0000
  12.000   1.4938   0.03947   0.03084  -0.0586   0.2009   1.0000
  12.250   1.5016   0.04018   0.03157  -0.0561   0.1948   1.0000
  12.500   1.5108   0.04117   0.03260  -0.0539   0.1890   1.0000
  12.750   1.5069   0.04243   0.03410  -0.0502   0.1839   1.0000
  13.000   1.5192   0.04312   0.03472  -0.0485   0.1779   1.0000
  13.250   1.5167   0.04460   0.03639  -0.0454   0.1727   1.0000
  13.500   1.5119   0.04604   0.03802  -0.0424   0.1673   1.0000
  13.750   1.5222   0.04687   0.03873  -0.0408   0.1605   1.0000
  14.000   1.5067   0.04907   0.04127  -0.0374   0.1554   1.0000
  14.250   1.5096   0.05015   0.04226  -0.0355   0.1482   1.0000
  14.500   1.4943   0.05285   0.04524  -0.0330   0.1422   1.0000
  14.750   1.4924   0.05449   0.04679  -0.0313   0.1343   1.0000
  15.000   1.4738   0.05797   0.05055  -0.0295   0.1276   1.0000
  15.250   1.4708   0.06019   0.05261  -0.0284   0.1194   1.0000
  15.500   1.4515   0.06433   0.05703  -0.0274   0.1132   1.0000
  15.750   1.4492   0.06698   0.05956  -0.0268   0.1066   1.0000
  16.000   1.4320   0.07153   0.06439  -0.0267   0.1019   1.0000
  16.250   1.4405   0.07327   0.06587  -0.0261   0.0961   1.0000
  16.500   1.4198   0.07875   0.07172  -0.0267   0.0934   1.0000
  16.750   1.4071   0.08347   0.07665  -0.0275   0.0903   1.0000
  17.000   1.4154   0.08532   0.07837  -0.0272   0.0864   1.0000
  17.250   1.4046   0.09013   0.08336  -0.0281   0.0842   1.0000
  17.500   1.3818   0.09682   0.09035  -0.0304   0.0827   1.0000
  17.750   1.3585   0.10396   0.09776  -0.0333   0.0815   1.0000
  18.000   1.3310   0.11225   0.10631  -0.0372   0.0807   1.0000
  18.250   1.2748   0.12662   0.12104  -0.0455   0.0816   1.0000
  18.500   1.3509   0.11572   0.10964  -0.0372   0.0754   1.0000
  18.750   1.3131   0.12630   0.12052  -0.0432   0.0754   1.0000
  19.000   0.9775   0.22871   0.22317  -0.1082   0.1265   1.0000
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