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GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il)
Reynolds number: 100,000
Max Cl/Cd: 55.9 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe278-il-100000.txt
Download as CSV file: xf-goe278-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 278 (DAIMLER IX) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3630   0.09868   0.09378  -0.0259   1.0000   0.0555
  -7.750  -0.3680   0.09754   0.09273  -0.0291   1.0000   0.0561
  -7.500  -0.3684   0.09618   0.09142  -0.0339   1.0000   0.0565
  -7.250  -0.3662   0.09453   0.08975  -0.0378   1.0000   0.0567
  -7.000  -0.3640   0.08804   0.08340  -0.0322   1.0000   0.0577
  -6.750  -0.3608   0.08434   0.07976  -0.0282   1.0000   0.0591
  -6.500  -0.3587   0.08160   0.07705  -0.0268   1.0000   0.0605
  -6.250  -0.3564   0.07901   0.07449  -0.0265   1.0000   0.0623
  -6.000  -0.3527   0.07639   0.07189  -0.0270   1.0000   0.0644
  -5.750  -0.3441   0.07386   0.06931  -0.0297   1.0000   0.0678
  -5.500  -0.3218   0.07231   0.06743  -0.0384   1.0000   0.0704
  -5.250  -0.3227   0.06735   0.06268  -0.0342   1.0000   0.0719
  -5.000  -0.3167   0.06438   0.05976  -0.0323   1.0000   0.0743
  -4.750  -0.3045   0.06159   0.05693  -0.0328   1.0000   0.0777
  -4.500  -0.2698   0.06014   0.05493  -0.0399   1.0000   0.0844
  -4.250  -0.2646   0.05542   0.05044  -0.0379   1.0000   0.0862
  -4.000  -0.2525   0.05263   0.04767  -0.0372   1.0000   0.0899
  -3.750  -0.2234   0.05045   0.04508  -0.0406   1.0000   0.0993
  -3.500  -0.2124   0.04729   0.04207  -0.0396   1.0000   0.1040
  -3.250  -0.1875   0.04492   0.03945  -0.0415   1.0000   0.1148
  -3.000  -0.1632   0.04327   0.03752  -0.0428   1.0000   0.1277
  -2.750  -0.1468   0.04038   0.03475  -0.0426   1.0000   0.1350
  -2.500  -0.1209   0.03884   0.03289  -0.0442   1.0000   0.1572
  -2.250  -0.0853   0.03599   0.03005  -0.0479   0.9957   0.1888
  -2.000  -0.0414   0.03327   0.02746  -0.0528   0.9867   0.2535
  -1.750  -0.0022   0.03102   0.02526  -0.0561   0.9787   0.3267
  -1.500   0.0392   0.02863   0.02298  -0.0590   0.9720   0.3895
  -1.250   0.0868   0.02670   0.02088  -0.0631   0.9627   0.4131
  -1.000   0.1691   0.02586   0.01858  -0.0722   0.9545   0.2624
  -0.750   0.2280   0.02464   0.01647  -0.0747   0.9454   0.1515
  -0.500   0.2745   0.02363   0.01507  -0.0766   0.9349   0.1216
  -0.250   0.3283   0.02282   0.01390  -0.0803   0.9279   0.1117
   0.000   0.3698   0.02156   0.01263  -0.0823   0.9161   0.1095
   0.250   0.4132   0.02046   0.01154  -0.0845   0.9049   0.1062
   0.500   0.4568   0.01943   0.01054  -0.0865   0.8948   0.1052
   0.750   0.4969   0.01846   0.00965  -0.0878   0.8832   0.1066
   1.000   0.5310   0.01775   0.00894  -0.0879   0.8680   0.1127
   1.250   0.5622   0.01704   0.00824  -0.0875   0.8500   0.1215
   1.500   0.5919   0.01647   0.00764  -0.0867   0.8293   0.1332
   1.750   0.6259   0.01399   0.00711  -0.0866   0.8098   1.0000
   2.000   0.6532   0.01383   0.00660  -0.0851   0.7834   1.0000
   2.250   0.6801   0.01368   0.00625  -0.0838   0.7533   1.0000
   2.500   0.7069   0.01362   0.00595  -0.0825   0.7200   1.0000
   2.750   0.7328   0.01375   0.00582  -0.0813   0.6846   1.0000
   3.000   0.7583   0.01406   0.00589  -0.0803   0.6508   1.0000
   3.250   0.7836   0.01452   0.00609  -0.0794   0.6205   1.0000
   3.500   0.8088   0.01502   0.00637  -0.0786   0.5946   1.0000
   3.750   0.8336   0.01549   0.00671  -0.0778   0.5708   1.0000
   4.000   0.8585   0.01595   0.00704  -0.0771   0.5501   1.0000
   4.250   0.8833   0.01639   0.00743  -0.0764   0.5312   1.0000
   4.500   0.9088   0.01686   0.00786  -0.0759   0.5160   1.0000
   4.750   0.9337   0.01729   0.00826  -0.0753   0.5003   1.0000
   5.000   0.9576   0.01766   0.00860  -0.0744   0.4819   1.0000
   5.250   0.9812   0.01801   0.00886  -0.0735   0.4633   1.0000
   5.500   1.0052   0.01842   0.00923  -0.0727   0.4469   1.0000
   5.750   1.0290   0.01885   0.00969  -0.0720   0.4310   1.0000
   6.000   1.0527   0.01928   0.01016  -0.0712   0.4157   1.0000
   6.250   1.0751   0.01966   0.01061  -0.0702   0.3979   1.0000
   6.500   1.0971   0.02001   0.01103  -0.0691   0.3792   1.0000
   6.750   1.1187   0.02034   0.01145  -0.0680   0.3606   1.0000
   7.000   1.1394   0.02065   0.01181  -0.0667   0.3403   1.0000
   7.250   1.1573   0.02083   0.01209  -0.0649   0.3111   1.0000
   7.500   1.1740   0.02100   0.01240  -0.0629   0.2588   1.0000
   7.750   1.1821   0.02261   0.01325  -0.0601   0.1478   1.0000
   8.000   1.1930   0.02452   0.01484  -0.0578   0.1097   1.0000
   8.250   1.2059   0.02605   0.01630  -0.0557   0.0973   1.0000
   8.500   1.2162   0.02767   0.01787  -0.0533   0.0895   1.0000
   8.750   1.2294   0.02905   0.01938  -0.0511   0.0849   1.0000
   9.000   1.2412   0.03060   0.02095  -0.0489   0.0806   1.0000
   9.250   1.2538   0.03260   0.02287  -0.0469   0.0765   1.0000
   9.500   1.2724   0.03424   0.02466  -0.0455   0.0731   1.0000
   9.750   1.2935   0.03619   0.02667  -0.0445   0.0699   1.0000
  10.000   1.3235   0.03971   0.02999  -0.0453   0.0655   1.0000
  10.250   1.3421   0.04185   0.03247  -0.0439   0.0639   1.0000
  10.500   1.3596   0.04447   0.03548  -0.0424   0.0625   1.0000
  10.750   1.3720   0.04713   0.03850  -0.0406   0.0606   1.0000
  11.000   1.3822   0.04995   0.04162  -0.0387   0.0587   1.0000
  11.250   1.3884   0.05325   0.04528  -0.0365   0.0581   1.0000
  11.500   1.3874   0.05677   0.04922  -0.0337   0.0581   1.0000
  11.750   1.3786   0.06033   0.05320  -0.0304   0.0585   1.0000
  12.000   1.3632   0.06377   0.05700  -0.0267   0.0588   1.0000
  12.250   1.3442   0.06747   0.06102  -0.0237   0.0592   1.0000
  12.500   1.3225   0.07162   0.06547  -0.0217   0.0597   1.0000
  12.750   1.2986   0.07633   0.07046  -0.0208   0.0603   1.0000
  13.000   1.2728   0.08173   0.07611  -0.0213   0.0610   1.0000
  13.250   1.2458   0.08795   0.08255  -0.0231   0.0617   1.0000
  13.500   1.2181   0.09507   0.08985  -0.0264   0.0625   1.0000
  13.750   1.1901   0.10312   0.09806  -0.0308   0.0633   1.0000
  14.000   1.1642   0.11183   0.10687  -0.0358   0.0642   1.0000
  14.250   1.1564   0.11904   0.11410  -0.0374   0.0653   1.0000
  14.500   0.8034   0.14564   0.14088  -0.0458   0.0874   1.0000
  14.750   0.8050   0.14959   0.14487  -0.0463   0.0900   1.0000
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