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EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/12 (eh2012-il)
Reynolds number: 100,000
Max Cl/Cd: 45.86 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2012-il-100000-n5.txt
Download as CSV file: xf-eh2012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/12                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5547   0.09666   0.09180  -0.0102   1.0000   0.0271
 -10.500  -0.6075   0.07575   0.07095  -0.0242   1.0000   0.0255
 -10.250  -0.6313   0.06746   0.06260  -0.0307   1.0000   0.0252
 -10.000  -0.6559   0.06160   0.05661  -0.0334   1.0000   0.0251
  -9.750  -0.6787   0.05711   0.05197  -0.0332   1.0000   0.0250
  -9.500  -0.7003   0.05295   0.04758  -0.0311   1.0000   0.0250
  -9.250  -0.7148   0.04858   0.04285  -0.0290   1.0000   0.0251
  -9.000  -0.7239   0.04425   0.03804  -0.0266   1.0000   0.0254
  -8.750  -0.7211   0.04131   0.03483  -0.0247   1.0000   0.0261
  -8.500  -0.7083   0.03999   0.03346  -0.0235   1.0000   0.0273
  -8.250  -0.6970   0.03809   0.03135  -0.0220   1.0000   0.0285
  -8.000  -0.6863   0.03561   0.02851  -0.0202   1.0000   0.0297
  -7.750  -0.6742   0.03290   0.02536  -0.0182   1.0000   0.0311
  -7.500  -0.6589   0.03045   0.02247  -0.0165   1.0000   0.0323
  -7.250  -0.6418   0.02852   0.02031  -0.0150   1.0000   0.0339
  -7.000  -0.6236   0.02759   0.01938  -0.0138   1.0000   0.0363
  -6.750  -0.6050   0.02641   0.01802  -0.0124   1.0000   0.0394
  -6.500  -0.5856   0.02497   0.01628  -0.0108   1.0000   0.0422
  -6.250  -0.5689   0.02387   0.01524  -0.0092   1.0000   0.0451
  -6.000  -0.5522   0.02314   0.01446  -0.0075   1.0000   0.0497
  -5.750  -0.5144   0.02188   0.01310  -0.0099   0.9830   0.0561
  -5.500  -0.4766   0.02101   0.01209  -0.0120   0.9636   0.0652
  -5.250  -0.4401   0.02012   0.01119  -0.0141   0.9434   0.0748
  -5.000  -0.4051   0.01932   0.01036  -0.0157   0.9217   0.0857
  -4.750  -0.3721   0.01864   0.00963  -0.0167   0.8993   0.0981
  -4.500  -0.3429   0.01804   0.00898  -0.0169   0.8761   0.1113
  -4.250  -0.3164   0.01753   0.00841  -0.0164   0.8536   0.1263
  -4.000  -0.2920   0.01707   0.00791  -0.0156   0.8317   0.1435
  -3.750  -0.2684   0.01663   0.00746  -0.0145   0.8112   0.1653
  -3.500  -0.2454   0.01619   0.00704  -0.0134   0.7923   0.1939
  -3.250  -0.2232   0.01568   0.00664  -0.0123   0.7740   0.2371
  -3.000  -0.2025   0.01503   0.00628  -0.0110   0.7569   0.3127
  -2.750  -0.1865   0.01402   0.00601  -0.0087   0.7410   0.4776
  -2.500  -0.1651   0.01346   0.00621  -0.0062   0.7261   0.6752
  -2.250  -0.1366   0.01355   0.00635  -0.0050   0.7113   0.7601
  -2.000  -0.1088   0.01373   0.00643  -0.0040   0.6970   0.8061
  -1.750  -0.0794   0.01393   0.00649  -0.0033   0.6831   0.8376
  -1.500  -0.0486   0.01416   0.00654  -0.0030   0.6698   0.8625
  -1.250  -0.0138   0.01445   0.00666  -0.0033   0.6565   0.8857
  -1.000   0.0277   0.01486   0.00691  -0.0047   0.6428   0.9123
  -0.750   0.0875   0.01526   0.00709  -0.0099   0.6281   0.9325
  -0.500   0.1239   0.01532   0.00700  -0.0115   0.6151   0.9429
  -0.250   0.1598   0.01531   0.00684  -0.0132   0.6025   0.9485
   0.000   0.1891   0.01533   0.00672  -0.0136   0.5909   0.9559
   0.250   0.2255   0.01530   0.00656  -0.0154   0.5796   0.9604
   0.500   0.2579   0.01531   0.00644  -0.0165   0.5683   0.9664
   0.750   0.2904   0.01531   0.00636  -0.0177   0.5570   0.9719
   1.000   0.3247   0.01530   0.00626  -0.0192   0.5460   0.9769
   1.250   0.3559   0.01534   0.00619  -0.0201   0.5360   0.9827
   1.500   0.3910   0.01532   0.00611  -0.0219   0.5251   0.9872
   1.750   0.4241   0.01534   0.00609  -0.0233   0.5145   0.9922
   2.000   0.4577   0.01536   0.00604  -0.0248   0.5049   0.9969
   2.250   0.4874   0.01541   0.00604  -0.0255   0.4950   1.0000
   2.500   0.5092   0.01549   0.00613  -0.0246   0.4858   1.0000
   2.750   0.5309   0.01560   0.00616  -0.0236   0.4780   1.0000
   3.000   0.5526   0.01572   0.00631  -0.0227   0.4684   1.0000
   3.250   0.5741   0.01586   0.00641  -0.0217   0.4605   1.0000
   3.500   0.5956   0.01601   0.00659  -0.0208   0.4518   1.0000
   3.750   0.6170   0.01618   0.00676  -0.0197   0.4435   1.0000
   4.000   0.6383   0.01636   0.00693  -0.0187   0.4354   1.0000
   4.250   0.6596   0.01656   0.00717  -0.0176   0.4270   1.0000
   4.500   0.6808   0.01677   0.00736  -0.0165   0.4194   1.0000
   4.750   0.7018   0.01700   0.00766  -0.0155   0.4107   1.0000
   5.000   0.7229   0.01723   0.00787  -0.0143   0.4034   1.0000
   5.250   0.7438   0.01748   0.00821  -0.0132   0.3946   1.0000
   5.500   0.7648   0.01775   0.00850  -0.0121   0.3872   1.0000
   5.750   0.7855   0.01802   0.00885  -0.0109   0.3786   1.0000
   6.000   0.8063   0.01832   0.00919  -0.0098   0.3709   1.0000
   6.250   0.8271   0.01862   0.00954  -0.0086   0.3628   1.0000
   6.500   0.8477   0.01895   0.00997  -0.0075   0.3546   1.0000
   6.750   0.8685   0.01926   0.01032  -0.0063   0.3469   1.0000
   7.000   0.8888   0.01963   0.01080  -0.0051   0.3381   1.0000
   7.250   0.9094   0.01997   0.01115  -0.0040   0.3305   1.0000
   7.500   0.9292   0.02036   0.01171  -0.0028   0.3211   1.0000
   7.750   0.9493   0.02074   0.01218  -0.0016   0.3127   1.0000
   8.000   0.9691   0.02113   0.01265  -0.0003   0.3038   1.0000
   8.250   0.9884   0.02158   0.01323   0.0009   0.2944   1.0000
   8.500   1.0078   0.02200   0.01371   0.0021   0.2855   1.0000
   8.750   1.0266   0.02245   0.01431   0.0034   0.2755   1.0000
   9.000   1.0447   0.02295   0.01496   0.0047   0.2649   1.0000
   9.250   1.0624   0.02345   0.01556   0.0061   0.2544   1.0000
   9.500   1.0787   0.02397   0.01617   0.0076   0.2423   1.0000
   9.750   1.0923   0.02452   0.01682   0.0093   0.2250   1.0000
  10.000   1.1027   0.02519   0.01752   0.0112   0.2043   1.0000
  10.250   1.1113   0.02606   0.01840   0.0132   0.1821   1.0000
  10.500   1.1178   0.02711   0.01943   0.0153   0.1629   1.0000
  10.750   1.1213   0.02829   0.02063   0.0177   0.1447   1.0000
  11.000   1.1189   0.02972   0.02204   0.0205   0.1264   1.0000
  11.250   1.1132   0.03159   0.02386   0.0228   0.1095   1.0000
  11.500   1.1064   0.03389   0.02615   0.0243   0.0948   1.0000
  11.750   1.0969   0.03678   0.02902   0.0250   0.0800   1.0000
  12.000   1.0859   0.04018   0.03242   0.0250   0.0689   1.0000
  12.250   1.0731   0.04413   0.03637   0.0244   0.0603   1.0000
  12.500   1.0619   0.04818   0.04049   0.0235   0.0537   1.0000
  12.750   1.0475   0.05284   0.04519   0.0221   0.0495   1.0000
  13.000   1.0364   0.05729   0.04973   0.0207   0.0459   1.0000
  13.250   1.0238   0.06207   0.05460   0.0191   0.0429   1.0000
  13.500   1.0114   0.06696   0.05956   0.0173   0.0411   1.0000
  13.750   0.9979   0.07210   0.06474   0.0154   0.0390   1.0000
  14.000   0.9901   0.07661   0.06937   0.0138   0.0371   1.0000
  14.250   0.9820   0.08130   0.07416   0.0120   0.0350   1.0000
  14.500   0.9743   0.08605   0.07899   0.0101   0.0334   1.0000
  14.750   0.9664   0.09093   0.08394   0.0081   0.0319   1.0000
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