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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.69 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe210-il-1000000.txt
Download as CSV file: xf-goe210-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3667   0.08778   0.08625  -0.0227   1.0000   0.0097
  -7.500  -0.3680   0.08501   0.08352  -0.0233   1.0000   0.0097
  -7.250  -0.3683   0.08211   0.08064  -0.0242   1.0000   0.0097
  -7.000  -0.3588   0.07704   0.07558  -0.0278   0.9986   0.0100
  -6.750  -0.3338   0.07325   0.07178  -0.0336   0.9962   0.0103
  -6.500  -0.3049   0.06903   0.06754  -0.0409   0.9938   0.0107
  -6.250  -0.2752   0.06457   0.06304  -0.0483   0.9899   0.0113
  -6.000  -0.2393   0.05938   0.05781  -0.0573   0.9864   0.0125
  -5.750  -0.1921   0.05292   0.05123  -0.0688   0.9816   0.0132
  -5.500  -0.1607   0.04796   0.04616  -0.0744   0.9735   0.0132
  -5.250  -0.1303   0.04304   0.04112  -0.0790   0.9643   0.0133
  -5.000  -0.1029   0.03534   0.03316  -0.0840   0.9521   0.0136
  -4.750  -0.0807   0.03371   0.03145  -0.0847   0.9368   0.0141
  -4.500  -0.0572   0.03214   0.02977  -0.0851   0.9159   0.0150
  -4.250  -0.0232   0.01439   0.01050  -0.0880   0.8939   0.0140
  -4.000   0.0024   0.01496   0.01102  -0.0875   0.8672   0.0145
  -3.750   0.0285   0.01423   0.01006  -0.0871   0.8456   0.0154
  -3.000   0.1097   0.01081   0.00577  -0.0863   0.8020   0.0195
  -2.750   0.1371   0.01082   0.00575  -0.0863   0.7909   0.0208
  -2.500   0.1648   0.01040   0.00519  -0.0861   0.7799   0.0222
  -2.250   0.1924   0.01024   0.00489  -0.0858   0.7667   0.0235
  -2.000   0.2195   0.00926   0.00373  -0.0856   0.7542   0.0254
  -1.750   0.2469   0.00895   0.00339  -0.0855   0.7433   0.0271
  -1.500   0.2747   0.00861   0.00300  -0.0854   0.7348   0.0282
  -1.000   0.3304   0.00811   0.00240  -0.0852   0.7184   0.0311
  -0.750   0.3582   0.00792   0.00216  -0.0851   0.7095   0.0319
  -0.500   0.3861   0.00775   0.00194  -0.0850   0.6997   0.0323
  -0.250   0.4140   0.00759   0.00175  -0.0849   0.6897   0.0326
   0.000   0.4419   0.00733   0.00141  -0.0849   0.6799   0.0337
   0.250   0.4698   0.00717   0.00118  -0.0848   0.6672   0.0356
   0.500   0.4976   0.00710   0.00106  -0.0847   0.6511   0.0378
   0.750   0.5252   0.00709   0.00099  -0.0845   0.6332   0.0398
   1.000   0.5529   0.00710   0.00094  -0.0844   0.6163   0.0417
   1.250   0.5804   0.00715   0.00092  -0.0843   0.5954   0.0452
   1.500   0.6075   0.00714   0.00096  -0.0842   0.5679   0.1057
   1.750   0.6301   0.00540   0.00118  -0.0837   0.5323   1.0000
   2.000   0.6559   0.00576   0.00127  -0.0833   0.4758   1.0000
   2.250   0.6807   0.00627   0.00143  -0.0829   0.4026   1.0000
   2.500   0.7061   0.00670   0.00161  -0.0826   0.3470   1.0000
   2.750   0.7317   0.00710   0.00177  -0.0823   0.3001   1.0000
   3.000   0.7575   0.00748   0.00194  -0.0820   0.2583   1.0000
   3.250   0.7834   0.00783   0.00211  -0.0817   0.2227   1.0000
   3.500   0.8095   0.00814   0.00229  -0.0815   0.1982   1.0000
   3.750   0.8360   0.00838   0.00245  -0.0813   0.1842   1.0000
   4.000   0.8628   0.00858   0.00260  -0.0812   0.1757   1.0000
   4.250   0.8896   0.00877   0.00276  -0.0810   0.1684   1.0000
   4.500   0.9163   0.00896   0.00293  -0.0809   0.1619   1.0000
   4.750   0.9429   0.00916   0.00310  -0.0807   0.1547   1.0000
   5.000   0.9691   0.00941   0.00329  -0.0805   0.1420   1.0000
   5.250   0.9952   0.00967   0.00347  -0.0803   0.1256   1.0000
   5.750   1.0427   0.01080   0.00424  -0.0792   0.0626   1.0000
   6.000   1.0681   0.01114   0.00456  -0.0788   0.0574   1.0000
   6.250   1.0939   0.01139   0.00483  -0.0786   0.0550   1.0000
   6.500   1.1199   0.01161   0.00509  -0.0783   0.0532   1.0000
   6.750   1.1453   0.01191   0.00539  -0.0780   0.0496   1.0000
   7.000   1.1700   0.01228   0.00574  -0.0776   0.0436   1.0000
   7.250   1.1948   0.01262   0.00599  -0.0773   0.0310   1.0000
   7.500   1.2163   0.01343   0.00669  -0.0763   0.0136   1.0000
   7.750   1.2404   0.01387   0.00721  -0.0758   0.0124   1.0000
   8.000   1.2635   0.01443   0.00784  -0.0751   0.0110   1.0000
   8.250   1.2847   0.01526   0.00878  -0.0740   0.0095   1.0000
   8.500   1.3073   0.01583   0.00941  -0.0733   0.0091   1.0000
   8.750   1.3297   0.01641   0.01006  -0.0725   0.0086   1.0000
   9.000   1.3513   0.01706   0.01079  -0.0717   0.0082   1.0000
   9.250   1.3721   0.01777   0.01158  -0.0707   0.0077   1.0000
   9.500   1.3920   0.01855   0.01243  -0.0696   0.0073   1.0000
   9.750   1.4100   0.01950   0.01346  -0.0683   0.0069   1.0000
  10.000   1.4158   0.02168   0.01584  -0.0653   0.0063   1.0000
  10.250   1.4364   0.02220   0.01643  -0.0643   0.0061   1.0000
  10.500   1.4534   0.02304   0.01735  -0.0629   0.0059   1.0000
  10.750   1.4679   0.02404   0.01845  -0.0612   0.0057   1.0000
  11.000   1.4801   0.02517   0.01968  -0.0592   0.0055   1.0000
  11.250   1.4886   0.02633   0.02094  -0.0566   0.0053   1.0000
  11.500   1.4946   0.02758   0.02229  -0.0538   0.0052   1.0000
  11.750   1.4994   0.02894   0.02376  -0.0511   0.0050   1.0000
  12.000   1.5031   0.03046   0.02540  -0.0485   0.0049   1.0000
  12.250   1.5062   0.03211   0.02715  -0.0463   0.0048   1.0000
  12.500   1.5085   0.03394   0.02909  -0.0443   0.0047   1.0000
  12.750   1.5098   0.03598   0.03124  -0.0426   0.0046   1.0000
  13.000   1.5094   0.03833   0.03371  -0.0413   0.0045   1.0000
  13.250   1.5073   0.04104   0.03653  -0.0403   0.0044   1.0000
  13.500   1.5030   0.04413   0.03974  -0.0396   0.0044   1.0000
  13.750   1.4956   0.04778   0.04353  -0.0391   0.0043   1.0000
  14.000   1.4852   0.05195   0.04783  -0.0391   0.0042   1.0000
  14.250   1.4724   0.05665   0.05268  -0.0394   0.0042   1.0000
  14.500   1.4570   0.06190   0.05809  -0.0401   0.0041   1.0000
  14.750   1.4389   0.06783   0.06418  -0.0414   0.0041   1.0000
  15.000   1.4210   0.07405   0.07057  -0.0433   0.0041   1.0000
  15.250   1.3990   0.08133   0.07803  -0.0458   0.0040   1.0000
  15.500   1.3856   0.08770   0.08453  -0.0487   0.0040   1.0000
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