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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 200,000
Max Cl/Cd: 77.86 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe210-il-200000-n5.txt
Download as CSV file: xf-goe210-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 210 (DAIMLER) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3311   0.08895   0.08571  -0.0238   1.0000   0.0192
  -7.000  -0.3324   0.08665   0.08348  -0.0236   1.0000   0.0195
  -6.750  -0.3331   0.08432   0.08121  -0.0236   1.0000   0.0198
  -6.500  -0.3151   0.08038   0.07729  -0.0289   0.9959   0.0206
  -6.250  -0.2856   0.07563   0.07251  -0.0373   0.9892   0.0219
  -6.000  -0.2443   0.07054   0.06732  -0.0500   0.9815   0.0234
  -5.500  -0.1818   0.05786   0.05448  -0.0654   0.9678   0.0152
  -5.250  -0.1468   0.05260   0.04909  -0.0726   0.9590   0.0153
  -4.250  -0.0023   0.03183   0.02730  -0.0928   0.9243   0.0163
  -4.000   0.0264   0.02929   0.02455  -0.0946   0.9132   0.0171
  -3.750   0.0555   0.02801   0.02312  -0.0958   0.9027   0.0193
  -3.500   0.0896   0.02441   0.01907  -0.0973   0.8934   0.0208
  -3.250   0.1232   0.02056   0.01458  -0.0982   0.8839   0.0224
  -3.000   0.1540   0.01832   0.01184  -0.0987   0.8740   0.0256
  -2.750   0.1835   0.01710   0.01037  -0.0990   0.8644   0.0277
  -2.500   0.2130   0.01604   0.00897  -0.0991   0.8553   0.0312
  -2.250   0.2419   0.01519   0.00778  -0.0989   0.8458   0.0337
  -2.000   0.2701   0.01400   0.00637  -0.0989   0.8373   0.0360
  -1.750   0.2979   0.01348   0.00577  -0.0988   0.8287   0.0393
  -1.500   0.3255   0.01290   0.00505  -0.0986   0.8204   0.0407
  -1.250   0.3531   0.01245   0.00448  -0.0983   0.8119   0.0422
  -1.000   0.3802   0.01211   0.00406  -0.0979   0.8011   0.0436
  -0.750   0.4071   0.01189   0.00375  -0.0976   0.7897   0.0458
  -0.500   0.4338   0.01160   0.00338  -0.0972   0.7763   0.0468
  -0.250   0.4604   0.01142   0.00310  -0.0967   0.7612   0.0477
   0.000   0.4872   0.01130   0.00288  -0.0963   0.7472   0.0493
   0.250   0.5142   0.01122   0.00274  -0.0959   0.7353   0.0519
   0.500   0.5412   0.01117   0.00263  -0.0956   0.7233   0.0575
   0.750   0.5680   0.01107   0.00257  -0.0952   0.7092   0.0914
   1.000   0.5910   0.00905   0.00263  -0.0943   0.6953   1.0000
   1.250   0.6179   0.00915   0.00260  -0.0939   0.6817   1.0000
   1.500   0.6449   0.00925   0.00261  -0.0936   0.6692   1.0000
   1.750   0.6718   0.00936   0.00264  -0.0933   0.6559   1.0000
   2.000   0.6985   0.00948   0.00267  -0.0930   0.6409   1.0000
   2.250   0.7250   0.00961   0.00273  -0.0926   0.6238   1.0000
   2.500   0.7512   0.00975   0.00279  -0.0922   0.6016   1.0000
   2.750   0.7763   0.00997   0.00283  -0.0915   0.5662   1.0000
   3.000   0.7997   0.01032   0.00292  -0.0906   0.5102   1.0000
   3.250   0.8211   0.01091   0.00309  -0.0894   0.4367   1.0000
   3.500   0.8428   0.01157   0.00338  -0.0884   0.3741   1.0000
   3.750   0.8656   0.01215   0.00370  -0.0877   0.3270   1.0000
   4.000   0.8890   0.01266   0.00405  -0.0871   0.2908   1.0000
   4.250   0.9132   0.01311   0.00437  -0.0866   0.2641   1.0000
   4.500   0.9374   0.01353   0.00471  -0.0861   0.2431   1.0000
   4.750   0.9619   0.01392   0.00507  -0.0856   0.2268   1.0000
   5.000   0.9863   0.01432   0.00543  -0.0851   0.2141   1.0000
   5.250   1.0104   0.01474   0.00581  -0.0846   0.2018   1.0000
   5.500   1.0349   0.01510   0.00620  -0.0842   0.1928   1.0000
   5.750   1.0591   0.01549   0.00663  -0.0837   0.1858   1.0000
   6.000   1.0835   0.01586   0.00706  -0.0832   0.1788   1.0000
   6.250   1.1072   0.01628   0.00751  -0.0826   0.1714   1.0000
   6.500   1.1303   0.01676   0.00798  -0.0820   0.1577   1.0000
   6.750   1.1537   0.01720   0.00844  -0.0814   0.1365   1.0000
   7.000   1.1751   0.01786   0.00891  -0.0807   0.0961   1.0000
   7.250   1.1929   0.01896   0.00973  -0.0795   0.0675   1.0000
   7.500   1.2137   0.01969   0.01047  -0.0786   0.0586   1.0000
   7.750   1.2348   0.02036   0.01120  -0.0777   0.0502   1.0000
   8.000   1.2560   0.02102   0.01195  -0.0768   0.0355   1.0000
   8.250   1.2716   0.02237   0.01314  -0.0752   0.0163   1.0000
   8.500   1.2893   0.02342   0.01433  -0.0737   0.0137   1.0000
   8.750   1.3063   0.02450   0.01563  -0.0721   0.0122   1.0000
   9.000   1.3211   0.02574   0.01710  -0.0702   0.0111   1.0000
   9.250   1.3362   0.02683   0.01838  -0.0686   0.0103   1.0000
   9.500   1.3489   0.02808   0.01981  -0.0666   0.0095   1.0000
   9.750   1.3586   0.02948   0.02139  -0.0643   0.0090   1.0000
  10.000   1.3645   0.03096   0.02309  -0.0615   0.0086   1.0000
  10.250   1.3685   0.03262   0.02492  -0.0587   0.0083   1.0000
  10.500   1.3705   0.03447   0.02693  -0.0559   0.0081   1.0000
  10.750   1.3707   0.03657   0.02919  -0.0533   0.0079   1.0000
  11.000   1.3689   0.03896   0.03173  -0.0510   0.0077   1.0000
  11.250   1.3652   0.04170   0.03462  -0.0489   0.0075   1.0000
  11.500   1.3594   0.04487   0.03793  -0.0470   0.0073   1.0000
  11.750   1.3578   0.04773   0.04096  -0.0457   0.0071   1.0000
  12.000   1.3590   0.05032   0.04376  -0.0448   0.0069   1.0000
  12.250   1.3584   0.05321   0.04686  -0.0442   0.0066   1.0000
  12.500   1.3554   0.05652   0.05036  -0.0438   0.0064   1.0000
  12.750   1.3506   0.06016   0.05420  -0.0437   0.0062   1.0000
  13.000   1.3440   0.06420   0.05843  -0.0439   0.0061   1.0000
  13.250   1.3360   0.06858   0.06300  -0.0444   0.0060   1.0000
  13.500   1.3267   0.07332   0.06794  -0.0453   0.0060   1.0000
  13.750   1.3163   0.07845   0.07327  -0.0468   0.0059   1.0000
  14.000   1.3047   0.08401   0.07902  -0.0487   0.0059   1.0000
  14.250   1.2924   0.09004   0.08524  -0.0512   0.0059   1.0000
  14.500   1.2795   0.09653   0.09192  -0.0542   0.0059   1.0000
  14.750   1.2661   0.10347   0.09904  -0.0577   0.0059   1.0000
  15.000   1.2524   0.11079   0.10654  -0.0616   0.0059   1.0000
  15.250   1.2385   0.11848   0.11440  -0.0658   0.0059   1.0000
  15.500   1.2244   0.12651   0.12258  -0.0704   0.0060   1.0000
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