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EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/10 (eh2010-il)
Reynolds number: 50,000
Max Cl/Cd: 30.81 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2010-il-50000-n5.txt
Download as CSV file: xf-eh2010-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/10                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5249   0.09784   0.09129  -0.0062   1.0000   0.0512
  -9.000  -0.5264   0.09308   0.08660  -0.0089   1.0000   0.0508
  -8.750  -0.5285   0.08832   0.08190  -0.0119   1.0000   0.0500
  -8.500  -0.5348   0.08322   0.07686  -0.0154   1.0000   0.0494
  -8.250  -0.5428   0.07868   0.07235  -0.0174   1.0000   0.0486
  -8.000  -0.5496   0.07400   0.06765  -0.0190   1.0000   0.0480
  -7.750  -0.5541   0.06935   0.06293  -0.0202   1.0000   0.0474
  -7.500  -0.5568   0.06470   0.05815  -0.0208   1.0000   0.0469
  -7.250  -0.5570   0.06012   0.05337  -0.0209   1.0000   0.0466
  -7.000  -0.5543   0.05571   0.04870  -0.0206   1.0000   0.0465
  -6.750  -0.5485   0.05156   0.04424  -0.0198   1.0000   0.0467
  -6.500  -0.5398   0.04770   0.04002  -0.0188   1.0000   0.0474
  -6.250  -0.5287   0.04426   0.03615  -0.0176   1.0000   0.0497
  -6.000  -0.5159   0.04079   0.03201  -0.0160   1.0000   0.0525
  -5.750  -0.5003   0.03759   0.02831  -0.0145   1.0000   0.0544
  -5.500  -0.4821   0.03508   0.02560  -0.0134   1.0000   0.0565
  -5.250  -0.4623   0.03289   0.02315  -0.0121   1.0000   0.0594
  -5.000  -0.4414   0.03097   0.02075  -0.0108   1.0000   0.0658
  -4.750  -0.4204   0.02916   0.01887  -0.0097   1.0000   0.0707
  -4.500  -0.3975   0.02745   0.01694  -0.0086   1.0000   0.0759
  -4.250  -0.3752   0.02604   0.01542  -0.0075   1.0000   0.0838
  -4.000  -0.3538   0.02497   0.01421  -0.0063   1.0000   0.0953
  -3.750  -0.3326   0.02393   0.01310  -0.0051   1.0000   0.1063
  -3.500  -0.3155   0.02319   0.01240  -0.0036   1.0000   0.1228
  -3.250  -0.2729   0.02201   0.01128  -0.0070   0.9808   0.1539
  -3.000  -0.2312   0.02078   0.01023  -0.0102   0.9592   0.2036
  -2.750  -0.1973   0.01908   0.00930  -0.0123   0.9373   0.3257
  -2.500  -0.1489   0.01784   0.01003  -0.0118   0.9271   0.8395
  -2.250  -0.0508   0.01848   0.01006  -0.0217   0.9200   0.9491
  -2.000   0.0594   0.01800   0.00897  -0.0371   0.9065   1.0000
  -1.750   0.0957   0.01790   0.00856  -0.0391   0.8711   1.0000
  -1.500   0.1225   0.01788   0.00822  -0.0390   0.8398   1.0000
  -1.250   0.1451   0.01790   0.00798  -0.0381   0.8133   1.0000
  -1.000   0.1659   0.01794   0.00781  -0.0368   0.7891   1.0000
  -0.750   0.1865   0.01801   0.00766  -0.0355   0.7677   1.0000
  -0.500   0.2070   0.01809   0.00753  -0.0342   0.7479   1.0000
  -0.250   0.2276   0.01819   0.00745  -0.0328   0.7302   1.0000
   0.000   0.2484   0.01831   0.00741  -0.0316   0.7129   1.0000
   0.250   0.2694   0.01845   0.00742  -0.0304   0.6965   1.0000
   0.500   0.2904   0.01860   0.00745  -0.0293   0.6810   1.0000
   0.750   0.3117   0.01877   0.00750  -0.0281   0.6663   1.0000
   1.000   0.3330   0.01895   0.00759  -0.0270   0.6522   1.0000
   1.250   0.3544   0.01915   0.00772  -0.0259   0.6386   1.0000
   1.500   0.3759   0.01937   0.00786  -0.0248   0.6255   1.0000
   1.750   0.3975   0.01960   0.00802  -0.0237   0.6129   1.0000
   2.000   0.4192   0.01983   0.00820  -0.0225   0.6009   1.0000
   2.250   0.4408   0.02009   0.00841  -0.0214   0.5890   1.0000
   2.500   0.4629   0.02038   0.00873  -0.0205   0.5766   1.0000
   2.750   0.4850   0.02069   0.00904  -0.0196   0.5647   1.0000
   3.000   0.5070   0.02102   0.00937  -0.0186   0.5532   1.0000
   3.250   0.5290   0.02134   0.00969  -0.0176   0.5422   1.0000
   3.500   0.5512   0.02164   0.01001  -0.0165   0.5321   1.0000
   3.750   0.5729   0.02204   0.01047  -0.0155   0.5203   1.0000
   4.000   0.5946   0.02246   0.01095  -0.0146   0.5092   1.0000
   4.250   0.6165   0.02286   0.01140  -0.0136   0.4986   1.0000
   4.500   0.6387   0.02323   0.01179  -0.0125   0.4887   1.0000
   4.750   0.6603   0.02368   0.01238  -0.0115   0.4778   1.0000
   5.000   0.6816   0.02418   0.01300  -0.0105   0.4667   1.0000
   5.250   0.7032   0.02466   0.01359  -0.0095   0.4563   1.0000
   5.500   0.7255   0.02508   0.01407  -0.0085   0.4465   1.0000
   5.750   0.7469   0.02560   0.01478  -0.0075   0.4357   1.0000
   6.000   0.7678   0.02620   0.01554  -0.0065   0.4244   1.0000
   6.250   0.7890   0.02677   0.01627  -0.0055   0.4137   1.0000
   6.500   0.8109   0.02726   0.01688  -0.0044   0.4034   1.0000
   6.750   0.8327   0.02776   0.01753  -0.0034   0.3927   1.0000
   7.000   0.8527   0.02844   0.01843  -0.0024   0.3807   1.0000
   7.250   0.8728   0.02911   0.01937  -0.0013   0.3689   1.0000
   7.500   0.8929   0.02974   0.02022  -0.0002   0.3569   1.0000
   7.750   0.9130   0.03034   0.02102   0.0010   0.3445   1.0000
   8.000   0.9327   0.03091   0.02181   0.0022   0.3315   1.0000
   8.250   0.9514   0.03148   0.02260   0.0035   0.3171   1.0000
   8.500   0.9689   0.03194   0.02328   0.0050   0.3005   1.0000
   8.750   0.9855   0.03199   0.02350   0.0069   0.2800   1.0000
   9.000   0.9938   0.03229   0.02393   0.0090   0.2500   1.0000
   9.250   0.9986   0.03300   0.02468   0.0112   0.2155   1.0000
   9.500   1.0012   0.03428   0.02596   0.0132   0.1818   1.0000
   9.750   0.9977   0.03621   0.02776   0.0152   0.1473   1.0000
  10.000   0.9866   0.03875   0.03009   0.0174   0.1200   1.0000
  10.250   0.9742   0.04182   0.03302   0.0187   0.1017   1.0000
  10.500   0.9623   0.04541   0.03651   0.0188   0.0890   1.0000
  10.750   0.9511   0.04932   0.04031   0.0183   0.0800   1.0000
  11.000   0.9426   0.05325   0.04427   0.0176   0.0710   1.0000
  11.250   0.9352   0.05714   0.04814   0.0168   0.0650   1.0000
  11.500   0.9296   0.06094   0.05198   0.0161   0.0595   1.0000
  11.750   0.9244   0.06467   0.05563   0.0154   0.0560   1.0000
  12.000   0.9224   0.06831   0.05948   0.0149   0.0512   1.0000
  12.250   0.9191   0.07207   0.06328   0.0139   0.0475   1.0000
  12.500   0.9172   0.07553   0.06669   0.0133   0.0449   1.0000
  12.750   0.9164   0.07942   0.07084   0.0126   0.0423   1.0000
  13.000   0.9159   0.08331   0.07496   0.0119   0.0407   1.0000
  13.250   0.9135   0.08765   0.07950   0.0108   0.0393   1.0000
  13.500   0.9092   0.09239   0.08443   0.0091   0.0383   1.0000
  13.750   0.9031   0.09759   0.08981   0.0070   0.0376   1.0000
  14.000   0.8949   0.10340   0.09578   0.0043   0.0368   1.0000
  14.250   0.8854   0.10966   0.10218   0.0012   0.0362   1.0000
  14.500   0.8678   0.11854   0.11129  -0.0036   0.0368   1.0000
  14.750   0.8418   0.13051   0.12343  -0.0103   0.0384   1.0000
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