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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 100,000
Max Cl/Cd: 58.22 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe379-il-100000.txt
Download as CSV file: xf-goe379-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.3103   0.08978   0.08560  -0.0297   1.0000   0.0502
  -6.250  -0.3102   0.08572   0.08161  -0.0257   1.0000   0.0510
  -6.000  -0.3121   0.08306   0.07901  -0.0232   1.0000   0.0521
  -5.750  -0.3149   0.08096   0.07697  -0.0214   1.0000   0.0530
  -5.500  -0.3174   0.07902   0.07508  -0.0201   1.0000   0.0540
  -5.250  -0.3183   0.07705   0.07314  -0.0193   1.0000   0.0551
  -5.000  -0.3172   0.07500   0.07112  -0.0189   1.0000   0.0565
  -4.750  -0.3132   0.07287   0.06900  -0.0193   1.0000   0.0583
  -4.500  -0.3039   0.07085   0.06694  -0.0209   1.0000   0.0606
  -4.000  -0.2409   0.06285   0.05874  -0.0327   0.9905   0.0653
  -3.750  -0.2030   0.05885   0.05462  -0.0381   0.9834   0.0724
  -3.500  -0.1524   0.05492   0.05041  -0.0468   0.9741   0.0784
  -3.250  -0.1181   0.05090   0.04634  -0.0506   0.9669   0.0843
  -3.000  -0.0697   0.04738   0.04250  -0.0571   0.9579   0.0926
  -2.750  -0.0231   0.04550   0.04018  -0.0620   0.9480   0.1046
  -2.500   0.0116   0.04079   0.03553  -0.0653   0.9420   0.1126
  -2.000   0.0882   0.03579   0.03002  -0.0712   0.9209   0.1610
  -1.750   0.1329   0.03269   0.02681  -0.0749   0.9144   0.1978
  -1.250   0.2345   0.02638   0.01895  -0.0790   0.8972   0.1022
  -1.000   0.2757   0.02377   0.01584  -0.0803   0.8883   0.0981
  -0.750   0.3126   0.02203   0.01359  -0.0807   0.8775   0.1060
  -0.500   0.3502   0.02052   0.01183  -0.0817   0.8672   0.1202
  -0.250   0.3899   0.01924   0.01046  -0.0831   0.8583   0.1388
   0.000   0.4218   0.01840   0.00954  -0.0831   0.8453   0.1542
   0.250   0.4527   0.01764   0.00874  -0.0829   0.8320   0.1697
   0.500   0.4856   0.01696   0.00804  -0.0831   0.8184   0.1891
   0.750   0.5150   0.01632   0.00749  -0.0828   0.8043   0.2363
   1.000   0.5951   0.01418   0.00661  -0.0930   0.7907   1.0000
   1.250   0.6204   0.01424   0.00644  -0.0918   0.7752   1.0000
   1.500   0.6440   0.01437   0.00642  -0.0905   0.7581   1.0000
   1.750   0.6679   0.01450   0.00640  -0.0892   0.7410   1.0000
   2.000   0.6921   0.01463   0.00642  -0.0880   0.7246   1.0000
   2.250   0.7166   0.01477   0.00643  -0.0869   0.7084   1.0000
   2.500   0.7412   0.01492   0.00645  -0.0858   0.6924   1.0000
   2.750   0.7650   0.01512   0.00656  -0.0847   0.6756   1.0000
   3.000   0.7886   0.01536   0.00673  -0.0836   0.6586   1.0000
   3.250   0.8126   0.01560   0.00694  -0.0826   0.6420   1.0000
   3.500   0.8367   0.01585   0.00712  -0.0816   0.6260   1.0000
   3.750   0.8609   0.01612   0.00731  -0.0806   0.6101   1.0000
   4.000   0.8851   0.01639   0.00750  -0.0796   0.5943   1.0000
   4.250   0.9077   0.01671   0.00780  -0.0785   0.5766   1.0000
   4.500   0.9308   0.01703   0.00816  -0.0774   0.5601   1.0000
   4.750   0.9543   0.01740   0.00853  -0.0764   0.5453   1.0000
   5.000   0.9780   0.01782   0.00898  -0.0756   0.5318   1.0000
   5.250   1.0016   0.01827   0.00947  -0.0747   0.5190   1.0000
   5.500   1.0254   0.01875   0.01001  -0.0739   0.5069   1.0000
   5.750   1.0495   0.01924   0.01060  -0.0731   0.4955   1.0000
   6.000   1.0733   0.01972   0.01117  -0.0723   0.4837   1.0000
   6.250   1.0927   0.01985   0.01141  -0.0705   0.4625   1.0000
   6.500   1.1100   0.01963   0.01117  -0.0681   0.4340   1.0000
   6.750   1.1306   0.01983   0.01144  -0.0665   0.4156   1.0000
   7.000   1.1445   0.01973   0.01140  -0.0637   0.3815   1.0000
   7.250   1.1579   0.01989   0.01162  -0.0608   0.3431   1.0000
   7.500   1.1665   0.02045   0.01202  -0.0574   0.2697   1.0000
   7.750   1.1606   0.02304   0.01339  -0.0528   0.0966   1.0000
   8.000   1.1594   0.02569   0.01556  -0.0489   0.0565   1.0000
   8.250   1.1684   0.02720   0.01720  -0.0461   0.0492   1.0000
   8.500   1.1724   0.02894   0.01908  -0.0428   0.0454   1.0000
   8.750   1.1726   0.03071   0.02101  -0.0390   0.0436   1.0000
   9.000   1.1732   0.03225   0.02272  -0.0352   0.0426   1.0000
   9.250   1.1734   0.03398   0.02458  -0.0317   0.0415   1.0000
   9.500   1.1771   0.03578   0.02646  -0.0288   0.0408   1.0000
   9.750   1.1867   0.03765   0.02844  -0.0265   0.0395   1.0000
  10.000   1.1983   0.03974   0.03051  -0.0247   0.0362   1.0000
  10.250   1.2360   0.04256   0.03334  -0.0250   0.0353   1.0000
  10.500   1.2783   0.04612   0.03720  -0.0262   0.0360   1.0000
  10.750   1.3022   0.04979   0.04134  -0.0253   0.0378   1.0000
  11.000   1.3103   0.05353   0.04556  -0.0230   0.0396   1.0000
  11.250   1.3134   0.05757   0.04998  -0.0206   0.0413   1.0000
  11.500   1.3188   0.06298   0.05567  -0.0192   0.0432   1.0000
  11.750   1.3228   0.06538   0.05843  -0.0162   0.0461   1.0000
  12.000   1.2944   0.06783   0.06128  -0.0119   0.0471   1.0000
  12.250   1.2701   0.07129   0.06509  -0.0097   0.0481   1.0000
  12.500   1.2475   0.07549   0.06957  -0.0088   0.0490   1.0000
  12.750   1.2243   0.08034   0.07467  -0.0091   0.0498   1.0000
  13.000   1.2012   0.08564   0.08018  -0.0104   0.0503   1.0000
  13.250   1.1771   0.09150   0.08624  -0.0127   0.0506   1.0000
  13.500   1.1534   0.09776   0.09266  -0.0161   0.0505   1.0000
  13.750   1.1281   0.10490   0.09995  -0.0205   0.0502   1.0000
  14.000   1.1032   0.11273   0.10789  -0.0257   0.0497   1.0000
  14.250   1.0772   0.12179   0.11705  -0.0320   0.0493   1.0000
  14.500   1.0508   0.13236   0.12768  -0.0393   0.0491   1.0000
  14.750   1.0225   0.14565   0.14095  -0.0478   0.0501   1.0000
  15.000   1.0104   0.15555   0.15080  -0.0527   0.0529   1.0000
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