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GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 758 AIRFOIL (goe758-il)
Reynolds number: 100,000
Max Cl/Cd: 45.41 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe758-il-100000.txt
Download as CSV file: xf-goe758-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 758 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2811   0.10415   0.09979  -0.0377   1.0000   0.1217
  -8.750  -0.3098   0.10448   0.10028  -0.0341   1.0000   0.1235
  -8.500  -0.3492   0.10394   0.09991  -0.0447   0.9892   0.1257
  -8.250  -0.2993   0.09741   0.09332  -0.0413   0.9890   0.1289
  -8.000  -0.2659   0.09327   0.08913  -0.0460   0.9825   0.1361
  -7.750  -0.2752   0.08789   0.08381  -0.0619   0.9616   0.1428
  -7.500  -0.2226   0.08422   0.08007  -0.0590   0.9610   0.1495
  -7.250  -0.2191   0.07815   0.07399  -0.0742   0.9436   0.1594
  -7.000  -0.1755   0.07484   0.07064  -0.0739   0.9415   0.1654
  -6.750  -0.1606   0.06939   0.06513  -0.0847   0.9271   0.1768
  -6.500  -0.1471   0.06492   0.06055  -0.0931   0.9126   0.1912
  -6.250  -0.1110   0.06245   0.05809  -0.0915   0.9059   0.1971
  -6.000  -0.0901   0.05915   0.05472  -0.0951   0.8951   0.2124
  -5.750  -0.0768   0.05660   0.05211  -0.0964   0.8817   0.2276
  -5.500  -0.0899   0.04157   0.03534  -0.1101   0.8641   0.1250
  -5.250  -0.0722   0.03672   0.03008  -0.1097   0.8541   0.1057
  -5.000  -0.0476   0.03349   0.02589  -0.1093   0.8464   0.0948
  -4.750  -0.0284   0.03152   0.02371  -0.1082   0.8362   0.0930
  -4.500   0.0003   0.02950   0.02133  -0.1082   0.8297   0.0913
  -4.250   0.0208   0.02832   0.01987  -0.1070   0.8201   0.0908
  -4.000   0.0502   0.02709   0.01833  -0.1068   0.8138   0.0924
  -3.750   0.0727   0.02630   0.01733  -0.1058   0.8050   0.0934
  -3.500   0.1015   0.02525   0.01608  -0.1054   0.7983   0.0940
  -3.250   0.1270   0.02455   0.01522  -0.1047   0.7911   0.0950
  -3.000   0.1526   0.02372   0.01436  -0.1040   0.7836   0.0967
  -2.750   0.1818   0.02280   0.01349  -0.1038   0.7785   0.1001
  -2.500   0.2008   0.02257   0.01331  -0.1023   0.7694   0.1048
  -2.250   0.2292   0.02191   0.01262  -0.1019   0.7641   0.1134
  -2.000   0.2483   0.02176   0.01249  -0.1004   0.7556   0.1249
  -1.750   0.2727   0.02080   0.01183  -0.0996   0.7497   0.1708
  -1.500   0.2863   0.01942   0.01205  -0.0970   0.7431   0.5551
  -1.250   0.3052   0.01922   0.01219  -0.0945   0.7359   0.6770
  -1.000   0.3368   0.01859   0.01194  -0.0931   0.7314   0.8200
  -0.750   0.4448   0.01833   0.01164  -0.1076   0.7229   0.9946
  -0.500   0.4711   0.01830   0.01133  -0.1078   0.7168   1.0000
  -0.250   0.4867   0.01869   0.01156  -0.1061   0.7087   1.0000
   0.000   0.5106   0.01879   0.01145  -0.1053   0.7022   1.0000
   0.250   0.5315   0.01910   0.01161  -0.1042   0.6951   1.0000
   0.500   0.5540   0.01934   0.01170  -0.1032   0.6879   1.0000
   0.750   0.5811   0.01946   0.01163  -0.1028   0.6821   1.0000
   1.000   0.5994   0.01994   0.01204  -0.1014   0.6736   1.0000
   1.250   0.6296   0.01994   0.01186  -0.1014   0.6683   1.0000
   1.500   0.6463   0.02055   0.01244  -0.0997   0.6593   1.0000
   1.750   0.6750   0.02064   0.01238  -0.0995   0.6533   1.0000
   2.000   0.6940   0.02119   0.01291  -0.0982   0.6451   1.0000
   2.250   0.7208   0.02139   0.01299  -0.0978   0.6383   1.0000
   2.500   0.7431   0.02184   0.01340  -0.0969   0.6309   1.0000
   2.750   0.7667   0.02220   0.01370  -0.0961   0.6231   1.0000
   3.000   0.7944   0.02244   0.01384  -0.0959   0.6169   1.0000
   3.250   0.8126   0.02304   0.01447  -0.0944   0.6078   1.0000
   3.500   0.8451   0.02308   0.01437  -0.0948   0.6024   1.0000
   3.750   0.8584   0.02391   0.01529  -0.0928   0.5924   1.0000
   4.000   0.8899   0.02395   0.01523  -0.0930   0.5867   1.0000
   4.250   0.9036   0.02480   0.01617  -0.0911   0.5771   1.0000
   4.500   0.9338   0.02488   0.01617  -0.0911   0.5711   1.0000
   4.750   0.9489   0.02568   0.01705  -0.0894   0.5620   1.0000
   5.000   0.9775   0.02580   0.01713  -0.0892   0.5556   1.0000
   5.250   0.9947   0.02652   0.01792  -0.0877   0.5475   1.0000
   5.500   1.0201   0.02678   0.01817  -0.0872   0.5404   1.0000
   5.750   1.0428   0.02723   0.01865  -0.0864   0.5336   1.0000
   6.000   1.0621   0.02777   0.01925  -0.0852   0.5256   1.0000
   6.250   1.0979   0.02760   0.01900  -0.0860   0.5211   1.0000
   6.500   1.1026   0.02888   0.02049  -0.0831   0.5115   1.0000
   6.750   1.1369   0.02869   0.02025  -0.0836   0.5065   1.0000
   7.000   1.1438   0.02994   0.02166  -0.0810   0.4979   1.0000
   7.250   1.1730   0.03002   0.02175  -0.0810   0.4924   1.0000
   7.500   1.1884   0.03088   0.02273  -0.0794   0.4857   1.0000
   7.750   1.2069   0.03150   0.02343  -0.0782   0.4788   1.0000
   8.000   1.2465   0.03111   0.02300  -0.0794   0.4747   1.0000
   8.250   1.2389   0.03316   0.02529  -0.0753   0.4661   1.0000
   8.500   1.2750   0.03279   0.02494  -0.0760   0.4609   1.0000
   8.750   1.2796   0.03412   0.02642  -0.0732   0.4534   1.0000
   9.000   1.3068   0.03410   0.02646  -0.0728   0.4470   1.0000
   9.250   1.3345   0.03425   0.02668  -0.0726   0.4412   1.0000
   9.500   1.3332   0.03578   0.02839  -0.0692   0.4337   1.0000
   9.750   1.3909   0.03426   0.02681  -0.0723   0.4283   1.0000
  10.000   1.3662   0.03688   0.02970  -0.0662   0.4203   1.0000
  10.250   1.4281   0.03455   0.02729  -0.0693   0.4117   1.0000
  10.500   1.4174   0.03612   0.02908  -0.0645   0.4034   1.0000
  10.750   1.4470   0.03496   0.02790  -0.0638   0.3918   1.0000
  11.000   1.4767   0.03379   0.02670  -0.0630   0.3792   1.0000
  11.250   1.4996   0.03302   0.02587  -0.0616   0.3662   1.0000
  11.500   1.4824   0.03426   0.02731  -0.0556   0.3581   1.0000
  11.750   1.4889   0.03435   0.02743  -0.0526   0.3467   1.0000
  12.000   1.4947   0.03448   0.02754  -0.0496   0.3345   1.0000
  12.250   1.4853   0.03577   0.02898  -0.0457   0.3248   1.0000
  12.500   1.4781   0.03715   0.03049  -0.0425   0.3147   1.0000
  12.750   1.4748   0.03837   0.03178  -0.0398   0.3032   1.0000
  13.000   1.4673   0.04003   0.03349  -0.0373   0.2907   1.0000
  13.250   1.4475   0.04317   0.03685  -0.0350   0.2798   1.0000
  13.500   1.4316   0.04632   0.04011  -0.0335   0.2669   1.0000
  13.750   1.4123   0.05012   0.04401  -0.0324   0.2512   1.0000
  14.000   1.3911   0.05450   0.04839  -0.0319   0.2321   1.0000
  14.250   1.3666   0.05990   0.05387  -0.0321   0.2125   1.0000
  14.500   1.3404   0.06575   0.05964  -0.0325   0.1859   1.0000
  14.750   1.3109   0.07233   0.06601  -0.0334   0.1551   1.0000
  15.000   1.2830   0.07909   0.07256  -0.0346   0.1322   1.0000
  15.250   1.2552   0.08621   0.07947  -0.0362   0.1151   1.0000
  15.500   1.2312   0.09301   0.08608  -0.0377   0.1023   1.0000
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