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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 500,000
Max Cl/Cd: 86.84 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe210-il-500000-n5.txt
Download as CSV file: xf-goe210-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2508   0.09074   0.08866  -0.0284   1.0000   0.0086
  -8.750  -0.2493   0.08766   0.08560  -0.0286   1.0000   0.0089
  -8.500  -0.2487   0.08457   0.08254  -0.0286   1.0000   0.0090
  -8.250  -0.2431   0.08074   0.07872  -0.0303   0.9978   0.0091
  -8.000  -0.2350   0.07649   0.07447  -0.0329   0.9945   0.0091
  -7.750  -0.3391   0.08952   0.08740  -0.0253   1.0000   0.0074
  -7.500  -0.3356   0.08694   0.08484  -0.0249   0.9987   0.0071
  -7.250  -0.3175   0.08269   0.08060  -0.0305   0.9928   0.0069
  -7.000  -0.2959   0.07802   0.07592  -0.0373   0.9869   0.0068
  -6.000  -0.1921   0.05726   0.05502  -0.0678   0.9485   0.0072
  -5.750  -0.1646   0.05237   0.05002  -0.0740   0.9346   0.0071
  -5.500  -0.1353   0.04711   0.04464  -0.0800   0.9174   0.0071
  -5.250  -0.1038   0.04112   0.03843  -0.0858   0.8974   0.0072
  -5.000  -0.0710   0.03410   0.03106  -0.0910   0.8765   0.0075
  -4.750  -0.0425   0.03030   0.02696  -0.0932   0.8575   0.0079
  -4.500  -0.0148   0.02765   0.02404  -0.0944   0.8420   0.0085
  -4.250   0.0187   0.01395   0.00877  -0.0970   0.8314   0.0107
  -4.000   0.0458   0.01267   0.00714  -0.0969   0.8200   0.0118
  -3.750   0.0732   0.01261   0.00698  -0.0967   0.8100   0.0129
  -3.500   0.1007   0.01209   0.00625  -0.0965   0.8009   0.0150
  -3.250   0.1283   0.01140   0.00535  -0.0964   0.7929   0.0166
  -3.000   0.1560   0.01139   0.00530  -0.0964   0.7850   0.0179
  -2.750   0.1837   0.01131   0.00513  -0.0963   0.7767   0.0203
  -2.500   0.2113   0.01105   0.00471  -0.0961   0.7678   0.0226
  -2.250   0.2390   0.01095   0.00451  -0.0959   0.7582   0.0239
  -2.000   0.2663   0.01025   0.00369  -0.0958   0.7498   0.0260
  -1.750   0.2938   0.00993   0.00330  -0.0957   0.7413   0.0275
  -1.500   0.3212   0.00971   0.00302  -0.0956   0.7305   0.0295
  -1.250   0.3484   0.00950   0.00271  -0.0954   0.7159   0.0310
  -1.000   0.3756   0.00931   0.00243  -0.0951   0.7007   0.0318
  -0.750   0.4032   0.00915   0.00218  -0.0950   0.6891   0.0324
  -0.500   0.4308   0.00901   0.00199  -0.0949   0.6799   0.0329
  -0.250   0.4585   0.00891   0.00185  -0.0948   0.6689   0.0335
   0.000   0.4860   0.00884   0.00171  -0.0947   0.6559   0.0339
   0.250   0.5136   0.00877   0.00158  -0.0946   0.6418   0.0339
   0.500   0.5410   0.00874   0.00148  -0.0944   0.6265   0.0340
   0.750   0.5685   0.00872   0.00140  -0.0943   0.6118   0.0343
   1.000   0.5956   0.00875   0.00134  -0.0941   0.5937   0.0351
   1.250   0.6226   0.00881   0.00131  -0.0939   0.5692   0.0373
   1.500   0.6479   0.00904   0.00134  -0.0934   0.5188   0.0439
   1.750   0.6710   0.00951   0.00152  -0.0927   0.4299   0.1018
   2.250   0.7160   0.00856   0.00206  -0.0914   0.3194   1.0000
   2.500   0.7417   0.00890   0.00222  -0.0911   0.2870   1.0000
   2.750   0.7675   0.00924   0.00238  -0.0909   0.2559   1.0000
   3.000   0.7932   0.00958   0.00257  -0.0906   0.2273   1.0000
   3.250   0.8190   0.00989   0.00275  -0.0903   0.2049   1.0000
   3.500   0.8449   0.01017   0.00294  -0.0901   0.1901   1.0000
   3.750   0.8711   0.01041   0.00313  -0.0898   0.1796   1.0000
   4.000   0.8972   0.01066   0.00334  -0.0896   0.1710   1.0000
   4.250   0.9234   0.01089   0.00354  -0.0894   0.1639   1.0000
   4.500   0.9493   0.01114   0.00376  -0.0891   0.1577   1.0000
   4.750   0.9756   0.01135   0.00399  -0.0889   0.1518   1.0000
   5.000   1.0012   0.01163   0.00423  -0.0886   0.1442   1.0000
   5.250   1.0273   0.01183   0.00446  -0.0884   0.1380   1.0000
   5.500   1.0524   0.01215   0.00473  -0.0880   0.1222   1.0000
   5.750   1.0727   0.01309   0.00530  -0.0871   0.0651   1.0000
   6.000   1.0969   0.01351   0.00570  -0.0866   0.0585   1.0000
   6.250   1.1214   0.01389   0.00608  -0.0861   0.0530   1.0000
   6.500   1.1464   0.01417   0.00641  -0.0858   0.0500   1.0000
   6.750   1.1702   0.01459   0.00684  -0.0853   0.0437   1.0000
   7.000   1.1938   0.01504   0.00724  -0.0847   0.0322   1.0000
   7.250   1.2144   0.01587   0.00795  -0.0837   0.0126   1.0000
   7.500   1.2376   0.01636   0.00852  -0.0830   0.0104   1.0000
   7.750   1.2599   0.01693   0.00920  -0.0822   0.0090   1.0000
   8.000   1.2805   0.01770   0.01010  -0.0812   0.0075   1.0000
   8.250   1.3019   0.01832   0.01082  -0.0803   0.0068   1.0000
   8.500   1.3229   0.01898   0.01158  -0.0793   0.0062   1.0000
   8.750   1.3431   0.01970   0.01240  -0.0782   0.0057   1.0000
   9.000   1.3621   0.02052   0.01331  -0.0771   0.0053   1.0000
   9.250   1.3779   0.02165   0.01455  -0.0754   0.0049   1.0000
   9.500   1.3946   0.02259   0.01560  -0.0739   0.0046   1.0000
   9.750   1.4116   0.02343   0.01657  -0.0725   0.0042   1.0000
  10.000   1.4265   0.02441   0.01766  -0.0708   0.0039   1.0000
  10.250   1.4391   0.02551   0.01888  -0.0689   0.0037   1.0000
  10.500   1.4484   0.02663   0.02011  -0.0664   0.0036   1.0000
  10.750   1.4559   0.02784   0.02141  -0.0638   0.0034   1.0000
  11.000   1.4611   0.02923   0.02291  -0.0611   0.0033   1.0000
  11.250   1.4634   0.03090   0.02471  -0.0584   0.0032   1.0000
  11.500   1.4612   0.03304   0.02699  -0.0555   0.0031   1.0000
  11.750   1.4597   0.03528   0.02938  -0.0532   0.0030   1.0000
  12.000   1.4602   0.03748   0.03174  -0.0513   0.0030   1.0000
  12.250   1.4596   0.03994   0.03436  -0.0498   0.0029   1.0000
  12.500   1.4570   0.04275   0.03733  -0.0486   0.0029   1.0000
  12.750   1.4534   0.04584   0.04059  -0.0477   0.0028   1.0000
  13.000   1.4480   0.04927   0.04423  -0.0471   0.0028   1.0000
  13.250   1.4413   0.05303   0.04816  -0.0468   0.0027   1.0000
  13.500   1.4331   0.05714   0.05244  -0.0469   0.0027   1.0000
  13.750   1.4237   0.06160   0.05707  -0.0474   0.0026   1.0000
  14.000   1.4131   0.06645   0.06209  -0.0484   0.0026   1.0000
  14.250   1.4013   0.07171   0.06753  -0.0498   0.0026   1.0000
  14.500   1.3888   0.07744   0.07343  -0.0517   0.0026   1.0000
  14.750   1.3757   0.08359   0.07975  -0.0541   0.0025   1.0000
  15.000   1.3616   0.09021   0.08652  -0.0570   0.0025   1.0000
  15.250   1.3475   0.09717   0.09365  -0.0602   0.0025   1.0000
  15.500   1.3327   0.10449   0.10111  -0.0637   0.0025   1.0000
  15.750   1.3173   0.11207   0.10885  -0.0674   0.0025   1.0000
  16.000   1.3026   0.11968   0.11659  -0.0713   0.0025   1.0000
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