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GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
Reynolds number: 500,000
Max Cl/Cd: 101.13 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe281-il-500000.txt
Download as CSV file: xf-goe281-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 281 (DAIMLER XII) AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3502   0.09435   0.09226  -0.0279   1.0000   0.0160
  -7.750  -0.3555   0.09209   0.09005  -0.0276   1.0000   0.0160
  -7.500  -0.3582   0.08845   0.08645  -0.0241   1.0000   0.0162
  -7.250  -0.3579   0.08600   0.08402  -0.0226   0.9997   0.0164
  -7.000  -0.3359   0.08178   0.07979  -0.0277   0.9971   0.0167
  -6.750  -0.3099   0.07732   0.07531  -0.0345   0.9944   0.0171
  -6.500  -0.2834   0.07282   0.07078  -0.0415   0.9904   0.0177
  -6.250  -0.2521   0.06792   0.06583  -0.0498   0.9868   0.0189
  -6.000  -0.1946   0.06080   0.05855  -0.0668   0.9838   0.0203
  -5.750  -0.1549   0.05510   0.05269  -0.0752   0.9796   0.0205
  -5.500  -0.1291   0.04857   0.04606  -0.0806   0.9751   0.0209
  -5.250  -0.1029   0.04549   0.04296  -0.0835   0.9715   0.0213
  -5.000  -0.0768   0.04261   0.04000  -0.0860   0.9652   0.0220
  -4.750  -0.0477   0.03945   0.03671  -0.0887   0.9586   0.0232
  -4.500  -0.0094   0.03625   0.03316  -0.0910   0.9506   0.0261
  -4.250   0.0206   0.03359   0.03013  -0.0918   0.9422   0.0264
  -4.000   0.0405   0.02823   0.02458  -0.0927   0.9312   0.0271
  -3.750   0.0628   0.02632   0.02259  -0.0927   0.9204   0.0278
  -3.500   0.0869   0.02465   0.02080  -0.0926   0.9090   0.0287
  -3.250   0.1126   0.02300   0.01894  -0.0925   0.8965   0.0303
  -3.000   0.1429   0.02313   0.01869  -0.0913   0.8826   0.0339
  -2.750   0.1686   0.01937   0.01453  -0.0916   0.8676   0.0353
  -2.500   0.1939   0.01797   0.01304  -0.0916   0.8507   0.0366
  -2.250   0.2205   0.01699   0.01189  -0.0914   0.8340   0.0386
  -2.000   0.2483   0.01637   0.01102  -0.0911   0.8179   0.0419
  -1.250   0.3308   0.01399   0.00793  -0.0908   0.7682   0.0587
  -1.000   0.3578   0.01321   0.00713  -0.0909   0.7511   0.0637
  -0.750   0.3852   0.01267   0.00648  -0.0909   0.7353   0.0764
  -0.500   0.4125   0.01222   0.00595  -0.0911   0.7208   0.0930
   0.000   0.4706   0.01132   0.00462  -0.0900   0.6922   0.0714
   0.250   0.4989   0.01058   0.00379  -0.0895   0.6787   0.0533
   0.500   0.5269   0.01026   0.00333  -0.0892   0.6657   0.0456
   0.750   0.5548   0.01020   0.00324  -0.0891   0.6535   0.0440
   1.000   0.5826   0.00979   0.00281  -0.0890   0.6419   0.0429
   1.250   0.6105   0.00962   0.00259  -0.0890   0.6288   0.0427
   1.500   0.6382   0.00952   0.00244  -0.0889   0.6144   0.0432
   1.750   0.6659   0.00948   0.00234  -0.0888   0.5987   0.0437
   2.000   0.6936   0.00946   0.00227  -0.0888   0.5822   0.0444
   2.250   0.7211   0.00947   0.00219  -0.0887   0.5639   0.0472
   2.500   0.7487   0.00952   0.00218  -0.0887   0.5417   0.0487
   2.750   0.7756   0.00964   0.00219  -0.0885   0.5125   0.0517
   3.000   0.7974   0.00795   0.00241  -0.0878   0.4817   1.0000
   3.250   0.8237   0.00824   0.00252  -0.0875   0.4571   1.0000
   3.500   0.8503   0.00850   0.00267  -0.0874   0.4400   1.0000
   3.750   0.8770   0.00873   0.00282  -0.0872   0.4260   1.0000
   4.000   0.9038   0.00896   0.00299  -0.0871   0.4136   1.0000
   4.250   0.9304   0.00920   0.00316  -0.0870   0.3995   1.0000
   4.500   0.9565   0.00948   0.00336  -0.0868   0.3775   1.0000
   4.750   0.9828   0.00972   0.00353  -0.0867   0.3552   1.0000
   5.000   1.0088   0.01000   0.00372  -0.0865   0.3315   1.0000
   5.250   1.0339   0.01040   0.00394  -0.0862   0.2937   1.0000
   5.500   1.0577   0.01094   0.00428  -0.0857   0.2550   1.0000
   5.750   1.0813   0.01150   0.00465  -0.0852   0.2228   1.0000
   6.000   1.1052   0.01201   0.00502  -0.0848   0.1946   1.0000
   6.250   1.1267   0.01282   0.00549  -0.0841   0.1399   1.0000
   6.500   1.1463   0.01383   0.00617  -0.0831   0.0903   1.0000
   6.750   1.1622   0.01530   0.00725  -0.0814   0.0231   1.0000
   7.000   1.1852   0.01586   0.00787  -0.0807   0.0201   1.0000
   7.250   1.2077   0.01648   0.00862  -0.0798   0.0179   1.0000
   7.500   1.2300   0.01707   0.00930  -0.0790   0.0169   1.0000
   7.750   1.2513   0.01776   0.01010  -0.0780   0.0161   1.0000
   8.000   1.2713   0.01855   0.01099  -0.0768   0.0153   1.0000
   8.250   1.2898   0.01944   0.01198  -0.0754   0.0147   1.0000
   8.500   1.3063   0.02046   0.01309  -0.0738   0.0141   1.0000
   8.750   1.3202   0.02163   0.01436  -0.0717   0.0137   1.0000
   9.000   1.3301   0.02306   0.01590  -0.0692   0.0132   1.0000
   9.250   1.3317   0.02502   0.01796  -0.0655   0.0126   1.0000
   9.500   1.3323   0.02685   0.01987  -0.0615   0.0123   1.0000
   9.750   1.3433   0.02782   0.02093  -0.0592   0.0120   1.0000
  10.000   1.3516   0.02913   0.02232  -0.0567   0.0119   1.0000
  10.250   1.3595   0.03058   0.02386  -0.0543   0.0117   1.0000
  10.500   1.3675   0.03216   0.02553  -0.0520   0.0116   1.0000
  10.750   1.3758   0.03385   0.02732  -0.0499   0.0114   1.0000
  11.000   1.3846   0.03567   0.02924  -0.0479   0.0113   1.0000
  11.250   1.3946   0.03770   0.03137  -0.0460   0.0114   1.0000
  11.500   1.4071   0.04008   0.03386  -0.0444   0.0115   1.0000
  14.500   1.3575   0.08242   0.07864  -0.0336   0.0149   1.0000
  14.750   1.3415   0.08795   0.08434  -0.0356   0.0148   1.0000
  15.000   1.3247   0.09401   0.09056  -0.0382   0.0148   1.0000
  15.250   1.3075   0.10051   0.09722  -0.0413   0.0148   1.0000
  15.500   1.2899   0.10756   0.10443  -0.0452   0.0147   1.0000
  15.750   1.2719   0.11524   0.11227  -0.0498   0.0148   1.0000
  16.000   1.2534   0.12346   0.12065  -0.0549   0.0148   1.0000
  16.250   1.2345   0.13226   0.12960  -0.0607   0.0149   1.0000
  16.500   1.2152   0.14179   0.13928  -0.0671   0.0151   1.0000
  16.750   1.1947   0.15237   0.14999  -0.0743   0.0154   1.0000
  17.000   1.1730   0.16410   0.16185  -0.0822   0.0158   1.0000
  17.250   1.1499   0.17704   0.17488  -0.0907   0.0164   1.0000
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