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GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 367 AIRFOIL (goe367-il)
Reynolds number: 200,000
Max Cl/Cd: 67.99 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe367-il-200000.txt
Download as CSV file: xf-goe367-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 367 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1760   0.09710   0.09336  -0.0846   0.9714   0.0872
  -9.750  -0.1571   0.09337   0.08961  -0.0887   0.9689   0.0896
  -9.500  -0.2049   0.08118   0.07742  -0.1110   0.9545   0.0949
  -9.250  -0.1673   0.08018   0.07643  -0.1062   0.9537   0.0957
  -9.000  -0.1484   0.07834   0.07458  -0.1048   0.9462   0.0966
  -8.750  -0.1324   0.07569   0.07191  -0.1058   0.9397   0.0981
  -8.500  -0.1288   0.07260   0.06881  -0.1074   0.9297   0.1000
  -8.250  -0.1450   0.06753   0.06369  -0.1124   0.9180   0.1033
  -8.000  -0.2869   0.04357   0.03822  -0.1130   0.8953   0.0752
  -7.750  -0.2704   0.04095   0.03550  -0.1123   0.8898   0.0743
  -7.500  -0.2574   0.03774   0.03205  -0.1113   0.8858   0.0735
  -7.250  -0.2528   0.03498   0.02900  -0.1086   0.8768   0.0728
  -7.000  -0.2406   0.03187   0.02545  -0.1068   0.8716   0.0728
  -6.750  -0.2228   0.02930   0.02239  -0.1054   0.8680   0.0737
  -6.500  -0.2097   0.02776   0.02049  -0.1032   0.8596   0.0745
  -6.250  -0.1878   0.02602   0.01842  -0.1022   0.8548   0.0753
  -6.000  -0.1608   0.02468   0.01700  -0.1022   0.8513   0.0766
  -5.750  -0.1392   0.02403   0.01629  -0.1012   0.8447   0.0779
  -5.500  -0.1142   0.02335   0.01552  -0.1007   0.8390   0.0798
  -5.250  -0.0866   0.02250   0.01449  -0.1004   0.8349   0.0822
  -5.000  -0.0605   0.02179   0.01353  -0.0999   0.8301   0.0843
  -4.750  -0.0369   0.02102   0.01282  -0.0992   0.8232   0.0864
  -4.500  -0.0089   0.02047   0.01224  -0.0991   0.8184   0.0891
  -4.250   0.0211   0.01992   0.01154  -0.0992   0.8147   0.0928
  -4.000   0.0431   0.01948   0.01110  -0.0982   0.8069   0.0962
  -3.750   0.0705   0.01906   0.01071  -0.0979   0.8014   0.1003
  -3.500   0.1007   0.01860   0.01011  -0.0980   0.7972   0.1055
  -3.250   0.1231   0.01824   0.00984  -0.0971   0.7893   0.1109
  -3.000   0.1507   0.01794   0.00947  -0.0968   0.7833   0.1187
  -2.750   0.1804   0.01737   0.00893  -0.0969   0.7788   0.1284
  -2.500   0.2020   0.01706   0.00869  -0.0957   0.7697   0.1399
  -2.250   0.2299   0.01659   0.00821  -0.0955   0.7635   0.1548
  -2.000   0.2553   0.01636   0.00796  -0.0949   0.7560   0.1684
  -1.750   0.2805   0.01598   0.00764  -0.0943   0.7484   0.1818
  -1.500   0.3095   0.01558   0.00723  -0.0944   0.7430   0.1953
  -1.250   0.3313   0.01540   0.00714  -0.0933   0.7339   0.2082
  -1.000   0.3587   0.01507   0.00683  -0.0931   0.7275   0.2257
  -0.750   0.3820   0.01479   0.00671  -0.0922   0.7196   0.2540
  -0.500   0.3993   0.01378   0.00653  -0.0905   0.7120   0.4544
  -0.250   0.4258   0.01313   0.00725  -0.0875   0.7063   0.9113
   0.000   0.4929   0.01361   0.00763  -0.0942   0.6971   0.9563
   0.250   0.5779   0.01370   0.00747  -0.1053   0.6901   0.9802
   0.500   0.6688   0.01351   0.00718  -0.1184   0.6790   1.0000
   0.750   0.6936   0.01346   0.00698  -0.1179   0.6715   1.0000
   1.000   0.7155   0.01349   0.00698  -0.1170   0.6610   1.0000
   1.250   0.7399   0.01349   0.00685  -0.1164   0.6531   1.0000
   1.500   0.7619   0.01353   0.00686  -0.1154   0.6429   1.0000
   1.750   0.7856   0.01356   0.00679  -0.1147   0.6345   1.0000
   2.000   0.8077   0.01362   0.00681  -0.1137   0.6245   1.0000
   2.250   0.8306   0.01369   0.00680  -0.1129   0.6156   1.0000
   2.500   0.8528   0.01377   0.00681  -0.1119   0.6060   1.0000
   2.750   0.8746   0.01388   0.00687  -0.1109   0.5965   1.0000
   3.000   0.8971   0.01398   0.00686  -0.1099   0.5874   1.0000
   3.250   0.9174   0.01413   0.00700  -0.1086   0.5774   1.0000
   3.500   0.9403   0.01428   0.00702  -0.1078   0.5690   1.0000
   3.750   0.9591   0.01448   0.00722  -0.1062   0.5592   1.0000
   4.000   0.9822   0.01467   0.00728  -0.1054   0.5511   1.0000
   4.250   0.9992   0.01488   0.00752  -0.1035   0.5411   1.0000
   4.500   1.0202   0.01510   0.00763  -0.1023   0.5322   1.0000
   4.750   1.0365   0.01531   0.00783  -0.1002   0.5221   1.0000
   5.000   1.0555   0.01555   0.00801  -0.0986   0.5132   1.0000
   5.250   1.0717   0.01578   0.00822  -0.0965   0.5042   1.0000
   5.500   1.0911   0.01605   0.00842  -0.0951   0.4967   1.0000
   5.750   1.1062   0.01629   0.00870  -0.0928   0.4890   1.0000
   6.000   1.1272   0.01658   0.00888  -0.0916   0.4827   1.0000
   6.250   1.1414   0.01685   0.00921  -0.0892   0.4759   1.0000
   6.500   1.1578   0.01711   0.00947  -0.0872   0.4696   1.0000
   6.750   1.1811   0.01743   0.00970  -0.0866   0.4644   1.0000
   7.000   1.1930   0.01771   0.01007  -0.0837   0.4585   1.0000
   7.250   1.2089   0.01797   0.01034  -0.0817   0.4526   1.0000
   7.500   1.2317   0.01828   0.01056  -0.0809   0.4470   1.0000
   7.750   1.2428   0.01856   0.01096  -0.0780   0.4410   1.0000
   8.000   1.2601   0.01885   0.01126  -0.0763   0.4354   1.0000
   8.250   1.2847   0.01918   0.01153  -0.0760   0.4307   1.0000
   8.500   1.3000   0.01955   0.01200  -0.0740   0.4260   1.0000
   8.750   1.3165   0.01988   0.01240  -0.0723   0.4208   1.0000
   9.000   1.3369   0.02020   0.01271  -0.0712   0.4159   1.0000
   9.250   1.3577   0.02058   0.01311  -0.0703   0.4112   1.0000
   9.500   1.3695   0.02096   0.01361  -0.0678   0.4063   1.0000
   9.750   1.3856   0.02132   0.01401  -0.0661   0.4015   1.0000
  10.000   1.4104   0.02167   0.01430  -0.0659   0.3965   1.0000
  10.250   1.4175   0.02215   0.01494  -0.0628   0.3914   1.0000
  10.500   1.4306   0.02260   0.01548  -0.0607   0.3863   1.0000
  10.750   1.4497   0.02296   0.01579  -0.0597   0.3803   1.0000
  11.000   1.4553   0.02357   0.01655  -0.0566   0.3740   1.0000
  11.250   1.4635   0.02413   0.01717  -0.0541   0.3668   1.0000
  11.500   1.4728   0.02476   0.01783  -0.0518   0.3593   1.0000
  11.750   1.4775   0.02555   0.01872  -0.0491   0.3515   1.0000
  12.000   1.4869   0.02630   0.01948  -0.0472   0.3438   1.0000
  12.250   1.4901   0.02733   0.02064  -0.0446   0.3354   1.0000
  12.500   1.4967   0.02831   0.02166  -0.0426   0.3270   1.0000
  12.750   1.4996   0.02956   0.02301  -0.0404   0.3176   1.0000
  13.000   1.5025   0.03092   0.02445  -0.0384   0.3076   1.0000
  13.250   1.5031   0.03248   0.02604  -0.0363   0.2962   1.0000
  13.500   1.5007   0.03440   0.02804  -0.0343   0.2822   1.0000
  13.750   1.4961   0.03668   0.03038  -0.0324   0.2638   1.0000
  14.000   1.4855   0.03961   0.03329  -0.0304   0.2368   1.0000
  14.250   1.4644   0.04370   0.03720  -0.0283   0.2024   1.0000
  14.500   1.4392   0.04848   0.04182  -0.0264   0.1809   1.0000
  14.750   1.4174   0.05324   0.04649  -0.0250   0.1667   1.0000
  15.000   1.4004   0.05773   0.05095  -0.0241   0.1545   1.0000
  15.250   1.3874   0.06194   0.05518  -0.0235   0.1434   1.0000
  15.500   1.3758   0.06613   0.05938  -0.0231   0.1336   1.0000
  15.750   1.3650   0.07035   0.06360  -0.0230   0.1246   1.0000
  16.000   1.3588   0.07412   0.06740  -0.0230   0.1162   1.0000
  16.250   1.3502   0.07821   0.07150  -0.0231   0.1098   1.0000
  16.500   1.3427   0.08223   0.07552  -0.0233   0.1040   1.0000
  16.750   1.3349   0.08627   0.07955  -0.0235   0.0992   1.0000
  17.000   1.3292   0.09004   0.08334  -0.0238   0.0945   1.0000
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