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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 100,000
Max Cl/Cd: 62.04 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe210-il-100000-n5.txt
Download as CSV file: xf-goe210-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3304   0.09710   0.09235  -0.0254   1.0000   0.0323
  -7.500  -0.3324   0.09521   0.09056  -0.0260   1.0000   0.0329
  -7.250  -0.3329   0.09330   0.08875  -0.0279   1.0000   0.0334
  -7.000  -0.3304   0.09111   0.08664  -0.0309   1.0000   0.0337
  -6.750  -0.3256   0.08868   0.08426  -0.0338   1.0000   0.0339
  -6.500  -0.3197   0.08607   0.08169  -0.0362   1.0000   0.0340
  -6.250  -0.3135   0.08338   0.07902  -0.0381   1.0000   0.0341
  -6.000  -0.3147   0.07943   0.07517  -0.0366   1.0000   0.0345
  -5.750  -0.3063   0.07519   0.07099  -0.0343   0.9967   0.0360
  -5.500  -0.2778   0.07074   0.06647  -0.0398   0.9903   0.0375
  -5.250  -0.2444   0.06616   0.06181  -0.0470   0.9833   0.0393
  -5.000  -0.2049   0.06134   0.05686  -0.0556   0.9770   0.0420
  -4.500  -0.1200   0.05129   0.04634  -0.0724   0.9617   0.0467
  -4.250  -0.0942   0.04836   0.04341  -0.0745   0.9556   0.0530
  -3.750  -0.0044   0.03723   0.03134  -0.0857   0.9429   0.0331
  -3.500   0.0366   0.03313   0.02678  -0.0895   0.9386   0.0332
  -3.250   0.0659   0.03065   0.02410  -0.0913   0.9298   0.0373
  -3.000   0.1045   0.02755   0.02053  -0.0938   0.9250   0.0381
  -2.750   0.1368   0.02525   0.01777  -0.0948   0.9167   0.0401
  -2.500   0.1739   0.02317   0.01509  -0.0962   0.9115   0.0442
  -2.250   0.2060   0.02153   0.01295  -0.0967   0.9036   0.0455
  -2.000   0.2387   0.02027   0.01161  -0.0980   0.8976   0.0510
  -1.750   0.2697   0.01914   0.01022  -0.0983   0.8901   0.0530
  -1.500   0.3023   0.01814   0.00899  -0.0989   0.8839   0.0550
  -1.250   0.3323   0.01751   0.00820  -0.0990   0.8762   0.0586
  -1.000   0.3633   0.01681   0.00752  -0.0996   0.8698   0.0628
  -0.750   0.3919   0.01629   0.00695  -0.0995   0.8617   0.0646
  -0.500   0.4227   0.01584   0.00641  -0.0998   0.8552   0.0671
  -0.250   0.4506   0.01557   0.00605  -0.0996   0.8463   0.0707
   0.000   0.4803   0.01527   0.00568  -0.0996   0.8383   0.0782
   0.250   0.5098   0.01494   0.00532  -0.0994   0.8272   0.1027
   0.500   0.5354   0.01267   0.00514  -0.0985   0.8137   1.0000
   0.750   0.5627   0.01269   0.00490  -0.0977   0.7981   1.0000
   1.000   0.5893   0.01275   0.00476  -0.0970   0.7824   1.0000
   1.250   0.6154   0.01284   0.00469  -0.0962   0.7664   1.0000
   1.500   0.6412   0.01293   0.00466  -0.0954   0.7495   1.0000
   1.750   0.6671   0.01304   0.00465  -0.0947   0.7332   1.0000
   2.000   0.6932   0.01315   0.00469  -0.0940   0.7184   1.0000
   2.250   0.7194   0.01328   0.00477  -0.0935   0.7042   1.0000
   2.500   0.7453   0.01341   0.00485  -0.0929   0.6885   1.0000
   2.750   0.7711   0.01354   0.00494  -0.0922   0.6715   1.0000
   3.000   0.7967   0.01368   0.00506  -0.0915   0.6533   1.0000
   3.250   0.8220   0.01383   0.00520  -0.0908   0.6327   1.0000
   3.500   0.8471   0.01399   0.00533  -0.0901   0.6091   1.0000
   3.750   0.8717   0.01418   0.00546  -0.0892   0.5793   1.0000
   4.000   0.8952   0.01443   0.00560  -0.0881   0.5362   1.0000
   4.250   0.9170   0.01486   0.00574  -0.0867   0.4778   1.0000
   4.500   0.9373   0.01551   0.00603  -0.0853   0.4157   1.0000
   4.750   0.9576   0.01624   0.00649  -0.0841   0.3651   1.0000
   5.000   0.9789   0.01692   0.00699  -0.0831   0.3291   1.0000
   5.250   1.0008   0.01756   0.00752  -0.0822   0.3020   1.0000
   5.500   1.0232   0.01815   0.00807  -0.0814   0.2798   1.0000
   5.750   1.0453   0.01877   0.00866  -0.0805   0.2606   1.0000
   6.000   1.0674   0.01937   0.00924  -0.0797   0.2445   1.0000
   6.250   1.0900   0.01993   0.00985  -0.0790   0.2322   1.0000
   6.500   1.1127   0.02048   0.01049  -0.0782   0.2218   1.0000
   6.750   1.1349   0.02108   0.01119  -0.0774   0.2118   1.0000
   7.250   1.1780   0.02233   0.01259  -0.0757   0.1893   1.0000
   7.500   1.1984   0.02300   0.01328  -0.0748   0.1700   1.0000
   7.750   1.2189   0.02365   0.01400  -0.0740   0.1498   1.0000
   8.000   1.2396   0.02430   0.01472  -0.0731   0.1294   1.0000
   8.250   1.2599   0.02502   0.01553  -0.0721   0.1013   1.0000
   8.500   1.2757   0.02622   0.01652  -0.0707   0.0760   1.0000
   8.750   1.2884   0.02785   0.01799  -0.0690   0.0561   1.0000
   9.250   1.3183   0.03051   0.02078  -0.0657   0.0247   1.0000
   9.500   1.3276   0.03236   0.02259  -0.0636   0.0202   1.0000
   9.750   1.3369   0.03403   0.02447  -0.0614   0.0185   1.0000
  10.000   1.3431   0.03570   0.02641  -0.0587   0.0177   1.0000
  10.250   1.3464   0.03753   0.02849  -0.0559   0.0171   1.0000
  10.500   1.3474   0.03954   0.03082  -0.0532   0.0165   1.0000
  10.750   1.3466   0.04177   0.03329  -0.0507   0.0160   1.0000
  11.000   1.3442   0.04425   0.03600  -0.0485   0.0154   1.0000
  11.250   1.3405   0.04699   0.03897  -0.0467   0.0147   1.0000
  11.500   1.3356   0.05003   0.04222  -0.0453   0.0142   1.0000
  11.750   1.3293   0.05341   0.04581  -0.0444   0.0137   1.0000
  12.000   1.3221   0.05707   0.04968  -0.0438   0.0133   1.0000
  12.250   1.3143   0.06100   0.05382  -0.0435   0.0131   1.0000
  12.500   1.3060   0.06519   0.05822  -0.0436   0.0129   1.0000
  12.750   1.2974   0.06963   0.06286  -0.0441   0.0128   1.0000
  13.000   1.2878   0.07438   0.06782  -0.0449   0.0127   1.0000
  13.250   1.2775   0.07946   0.07310  -0.0461   0.0126   1.0000
  13.500   1.2665   0.08489   0.07874  -0.0478   0.0125   1.0000
  13.750   1.2548   0.09071   0.08476  -0.0500   0.0125   1.0000
  14.000   1.2424   0.09698   0.09124  -0.0527   0.0125   1.0000
  14.250   1.2297   0.10369   0.09814  -0.0560   0.0125   1.0000
  14.500   1.2167   0.11081   0.10545  -0.0597   0.0125   1.0000
  14.750   1.2034   0.11839   0.11320  -0.0638   0.0125   1.0000
  15.000   1.1901   0.12631   0.12130  -0.0683   0.0126   1.0000
  15.250   1.1765   0.13463   0.12978  -0.0731   0.0127   1.0000
  15.500   1.1623   0.14351   0.13881  -0.0783   0.0129   1.0000
  15.750   1.1477   0.15298   0.14842  -0.0839   0.0131   1.0000
  16.000   1.1319   0.16349   0.15907  -0.0900   0.0134   1.0000
  16.250   1.1132   0.17595   0.17162  -0.0969   0.0139   1.0000
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