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EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/12 (eh2012-il)
Reynolds number: 500,000
Max Cl/Cd: 85.36 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2012-il-500000-n5.txt
Download as CSV file: xf-eh2012-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8108   0.09003   0.08753  -0.0099   1.0000   0.0075
 -13.750  -0.9108   0.06215   0.05933  -0.0285   1.0000   0.0072
 -13.500  -0.9486   0.05056   0.04745  -0.0379   1.0000   0.0071
 -13.250  -0.9687   0.04511   0.04180  -0.0404   1.0000   0.0072
 -13.000  -0.9879   0.04084   0.03732  -0.0407   1.0000   0.0071
 -12.750  -0.9991   0.03785   0.03414  -0.0396   1.0000   0.0071
 -12.500  -1.0042   0.03564   0.03177  -0.0378   1.0000   0.0073
 -12.250  -1.0101   0.03352   0.02946  -0.0352   1.0000   0.0073
 -12.000  -1.0125   0.03174   0.02751  -0.0322   1.0000   0.0074
 -11.750  -1.0112   0.03022   0.02581  -0.0292   1.0000   0.0075
 -11.500  -1.0043   0.02874   0.02416  -0.0270   1.0000   0.0076
 -11.250  -0.9945   0.02732   0.02256  -0.0250   1.0000   0.0078
 -11.000  -0.9820   0.02605   0.02112  -0.0232   1.0000   0.0079
 -10.750  -0.9679   0.02483   0.01974  -0.0216   1.0000   0.0080
 -10.500  -0.9521   0.02375   0.01850  -0.0201   1.0000   0.0081
 -10.250  -0.9357   0.02267   0.01728  -0.0187   1.0000   0.0083
 -10.000  -0.9203   0.02145   0.01595  -0.0171   1.0000   0.0085
  -9.750  -0.9020   0.02053   0.01493  -0.0158   1.0000   0.0088
  -9.500  -0.8824   0.01973   0.01406  -0.0147   1.0000   0.0090
  -9.250  -0.8621   0.01901   0.01325  -0.0136   1.0000   0.0093
  -9.000  -0.8414   0.01832   0.01250  -0.0125   1.0000   0.0096
  -8.750  -0.8204   0.01768   0.01176  -0.0114   1.0000   0.0100
  -8.500  -0.7993   0.01707   0.01108  -0.0103   1.0000   0.0104
  -8.250  -0.7726   0.01647   0.01040  -0.0104   0.9912   0.0109
  -8.000  -0.7381   0.01576   0.00961  -0.0121   0.9675   0.0115
  -7.750  -0.7032   0.01505   0.00883  -0.0139   0.9379   0.0125
  -7.500  -0.6749   0.01459   0.00824  -0.0140   0.9018   0.0133
  -7.250  -0.6521   0.01423   0.00772  -0.0129   0.8683   0.0141
  -7.000  -0.6293   0.01392   0.00725  -0.0118   0.8389   0.0149
  -6.750  -0.6066   0.01351   0.00673  -0.0108   0.8132   0.0163
  -6.500  -0.5828   0.01320   0.00631  -0.0099   0.7898   0.0180
  -6.250  -0.5583   0.01294   0.00591  -0.0092   0.7683   0.0196
  -6.000  -0.5341   0.01262   0.00552  -0.0085   0.7481   0.0226
  -5.750  -0.5089   0.01239   0.00519  -0.0079   0.7298   0.0256
  -5.500  -0.4840   0.01210   0.00486  -0.0073   0.7124   0.0300
  -5.250  -0.4585   0.01189   0.00457  -0.0068   0.6962   0.0342
  -5.000  -0.4331   0.01166   0.00429  -0.0063   0.6806   0.0399
  -4.750  -0.4073   0.01146   0.00403  -0.0059   0.6660   0.0452
  -4.500  -0.3813   0.01127   0.00380  -0.0055   0.6523   0.0515
  -4.250  -0.3554   0.01108   0.00358  -0.0051   0.6390   0.0586
  -4.000  -0.3291   0.01093   0.00337  -0.0047   0.6262   0.0661
  -3.750  -0.3029   0.01075   0.00318  -0.0044   0.6137   0.0756
  -3.500  -0.2766   0.01058   0.00299  -0.0041   0.6018   0.0855
  -3.250  -0.2502   0.01043   0.00282  -0.0037   0.5906   0.0968
  -3.000  -0.2238   0.01029   0.00266  -0.0034   0.5794   0.1095
  -2.750  -0.1975   0.01013   0.00251  -0.0031   0.5682   0.1256
  -2.500  -0.1710   0.00997   0.00237  -0.0028   0.5578   0.1449
  -2.250  -0.1447   0.00981   0.00224  -0.0025   0.5474   0.1686
  -1.750  -0.0929   0.00939   0.00200  -0.0019   0.5276   0.2440
  -1.500  -0.0683   0.00904   0.00187  -0.0014   0.5188   0.3171
  -1.250  -0.0453   0.00856   0.00173  -0.0006   0.5097   0.4236
  -1.000  -0.0244   0.00796   0.00161   0.0006   0.5011   0.5626
  -0.500   0.0227   0.00746   0.00158   0.0026   0.4843   0.7174
  -0.250   0.0484   0.00740   0.00160   0.0032   0.4759   0.7565
   0.000   0.0747   0.00738   0.00162   0.0037   0.4674   0.7866
   0.250   0.1008   0.00738   0.00167   0.0043   0.4596   0.8170
   0.500   0.1269   0.00741   0.00173   0.0050   0.4512   0.8441
   0.750   0.1530   0.00745   0.00179   0.0056   0.4434   0.8660
   1.000   0.1791   0.00753   0.00187   0.0063   0.4354   0.8856
   1.250   0.2058   0.00760   0.00193   0.0067   0.4276   0.8990
   1.500   0.2334   0.00767   0.00197   0.0069   0.4199   0.9055
   1.750   0.2609   0.00774   0.00200   0.0070   0.4124   0.9118
   2.250   0.3169   0.00790   0.00210   0.0071   0.3971   0.9231
   2.750   0.3739   0.00809   0.00224   0.0069   0.3820   0.9333
   3.000   0.4012   0.00820   0.00230   0.0071   0.3746   0.9395
   3.250   0.4309   0.00829   0.00239   0.0067   0.3668   0.9436
   3.500   0.4608   0.00842   0.00249   0.0062   0.3595   0.9480
   3.750   0.4893   0.00852   0.00258   0.0061   0.3521   0.9532
   4.000   0.5191   0.00865   0.00269   0.0056   0.3446   0.9573
   4.250   0.5508   0.00877   0.00281   0.0047   0.3367   0.9604
   4.500   0.5814   0.00892   0.00293   0.0041   0.3293   0.9643
   4.750   0.6100   0.00904   0.00306   0.0039   0.3220   0.9691
   5.000   0.6421   0.00920   0.00320   0.0028   0.3146   0.9716
   5.250   0.6748   0.00935   0.00335   0.0016   0.3065   0.9740
   5.500   0.7069   0.00951   0.00351   0.0006   0.2988   0.9766
   5.750   0.7380   0.00969   0.00369  -0.0003   0.2900   0.9797
   6.000   0.7680   0.00986   0.00387  -0.0009   0.2821   0.9831
   6.500   0.8338   0.01024   0.00427  -0.0035   0.2649   0.9869
   6.750   0.8654   0.01046   0.00449  -0.0046   0.2561   0.9895
   7.000   0.8961   0.01070   0.00472  -0.0055   0.2464   0.9923
   7.250   0.9272   0.01093   0.00497  -0.0064   0.2361   0.9947
   7.500   0.9586   0.01123   0.00525  -0.0076   0.2214   0.9971
   7.750   0.9890   0.01164   0.00557  -0.0087   0.2004   0.9995
   8.000   1.0091   0.01210   0.00593  -0.0076   0.1774   1.0000
   8.250   1.0260   0.01259   0.00633  -0.0060   0.1555   1.0000
   8.500   1.0430   0.01310   0.00676  -0.0043   0.1366   1.0000
   8.750   1.0595   0.01367   0.00724  -0.0026   0.1170   1.0000
   9.000   1.0745   0.01435   0.00781  -0.0008   0.0956   1.0000
   9.250   1.0899   0.01502   0.00839   0.0009   0.0769   1.0000
   9.500   1.1032   0.01583   0.00909   0.0029   0.0573   1.0000
   9.750   1.1158   0.01669   0.00987   0.0049   0.0401   1.0000
  10.000   1.1278   0.01758   0.01070   0.0070   0.0264   1.0000
  10.250   1.1401   0.01841   0.01151   0.0089   0.0191   1.0000
  10.500   1.1535   0.01913   0.01226   0.0107   0.0158   1.0000
  10.750   1.1649   0.01993   0.01309   0.0127   0.0136   1.0000
  11.000   1.1745   0.02063   0.01386   0.0151   0.0126   1.0000
  11.250   1.1815   0.02141   0.01470   0.0177   0.0116   1.0000
  11.500   1.1876   0.02234   0.01571   0.0200   0.0109   1.0000
  11.750   1.1905   0.02360   0.01704   0.0221   0.0101   1.0000
  12.000   1.1956   0.02490   0.01841   0.0236   0.0095   1.0000
  12.250   1.2007   0.02635   0.01996   0.0247   0.0092   1.0000
  12.500   1.2045   0.02808   0.02179   0.0255   0.0087   1.0000
  12.750   1.2079   0.03001   0.02380   0.0259   0.0084   1.0000
  13.000   1.2101   0.03220   0.02608   0.0260   0.0082   1.0000
  13.250   1.2103   0.03472   0.02869   0.0259   0.0077   1.0000
  13.500   1.2091   0.03752   0.03158   0.0255   0.0075   1.0000
  13.750   1.2028   0.04100   0.03516   0.0249   0.0072   1.0000
  14.000   1.1975   0.04448   0.03876   0.0240   0.0071   1.0000
  14.250   1.1943   0.04778   0.04215   0.0232   0.0070   1.0000
  14.500   1.1889   0.05142   0.04592   0.0222   0.0069   1.0000
  14.750   1.1850   0.05494   0.04954   0.0212   0.0066   1.0000
  15.000   1.1756   0.05924   0.05394   0.0198   0.0066   1.0000
  15.250   1.1681   0.06346   0.05827   0.0183   0.0066   1.0000
  15.500   1.1633   0.06741   0.06232   0.0169   0.0063   1.0000
  15.750   1.1543   0.07208   0.06709   0.0151   0.0064   1.0000
  16.000   1.1470   0.07665   0.07176   0.0133   0.0062   1.0000
  16.250   1.1391   0.08135   0.07656   0.0113   0.0062   1.0000
  16.500   1.1318   0.08611   0.08141   0.0093   0.0060   1.0000
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