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EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EH 3.0/12 (eh3012-il)
Reynolds number: 200,000
Max Cl/Cd: 65.32 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh3012-il-200000-n5.txt
Download as CSV file: xf-eh3012-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 3.0/12                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5057   0.09350   0.09008  -0.0092   1.0000   0.0130
 -10.250  -0.7278   0.05105   0.04735  -0.0294   1.0000   0.0115
 -10.000  -0.7735   0.04024   0.03586  -0.0268   1.0000   0.0113
  -9.750  -0.7853   0.03459   0.02955  -0.0240   1.0000   0.0115
  -9.500  -0.7724   0.03303   0.02786  -0.0226   1.0000   0.0117
  -9.250  -0.7541   0.03232   0.02711  -0.0217   1.0000   0.0122
  -9.000  -0.7414   0.03035   0.02488  -0.0202   1.0000   0.0124
  -8.750  -0.7265   0.02863   0.02291  -0.0187   1.0000   0.0126
  -8.500  -0.7100   0.02710   0.02115  -0.0174   1.0000   0.0130
  -8.250  -0.6927   0.02562   0.01942  -0.0160   1.0000   0.0132
  -8.000  -0.6666   0.02414   0.01768  -0.0164   0.9705   0.0137
  -7.750  -0.6301   0.02278   0.01600  -0.0187   0.9174   0.0144
  -7.500  -0.6006   0.02177   0.01467  -0.0191   0.8739   0.0151
  -7.250  -0.5775   0.02115   0.01386  -0.0182   0.8377   0.0157
  -7.000  -0.5551   0.02058   0.01311  -0.0172   0.8081   0.0162
  -6.750  -0.5323   0.02002   0.01234  -0.0162   0.7832   0.0169
  -6.500  -0.5096   0.01938   0.01149  -0.0152   0.7617   0.0176
  -6.250  -0.4863   0.01879   0.01067  -0.0142   0.7441   0.0181
  -6.000  -0.4625   0.01824   0.00994  -0.0134   0.7260   0.0188
  -5.750  -0.4384   0.01781   0.00940  -0.0127   0.7100   0.0202
  -5.500  -0.4141   0.01737   0.00881  -0.0120   0.6944   0.0213
  -5.250  -0.3895   0.01695   0.00826  -0.0113   0.6801   0.0228
  -5.000  -0.3649   0.01658   0.00779  -0.0107   0.6664   0.0253
  -4.750  -0.3398   0.01626   0.00737  -0.0102   0.6534   0.0282
  -4.500  -0.3148   0.01593   0.00700  -0.0096   0.6412   0.0321
  -4.250  -0.2895   0.01563   0.00661  -0.0091   0.6300   0.0362
  -3.750  -0.2398   0.01489   0.00579  -0.0078   0.6090   0.0466
  -3.500  -0.2146   0.01460   0.00546  -0.0072   0.5992   0.0552
  -3.250  -0.1894   0.01437   0.00518  -0.0067   0.5892   0.0664
  -3.000  -0.1637   0.01416   0.00494  -0.0062   0.5796   0.0778
  -2.750  -0.1383   0.01397   0.00471  -0.0057   0.5709   0.0895
  -2.500  -0.1128   0.01376   0.00450  -0.0052   0.5616   0.1017
  -2.250  -0.0875   0.01358   0.00431  -0.0047   0.5535   0.1171
  -2.000  -0.0620   0.01339   0.00412  -0.0043   0.5448   0.1356
  -1.750  -0.0370   0.01318   0.00393  -0.0037   0.5370   0.1551
  -1.500  -0.0120   0.01296   0.00375  -0.0032   0.5290   0.1829
  -1.250   0.0116   0.01263   0.00357  -0.0024   0.5220   0.2358
  -1.000   0.0216   0.01121   0.00331   0.0006   0.5151   0.5388
  -0.750   0.0389   0.01058   0.00356   0.0037   0.5086   0.7890
  -0.500   0.0678   0.01064   0.00367   0.0041   0.5009   0.8424
  -0.250   0.0980   0.01078   0.00374   0.0042   0.4939   0.8739
   0.000   0.1319   0.01094   0.00385   0.0035   0.4864   0.8964
   0.250   0.1661   0.01113   0.00394   0.0026   0.4790   0.9139
   0.500   0.2031   0.01133   0.00406   0.0012   0.4719   0.9280
   0.750   0.2401   0.01153   0.00416  -0.0004   0.4645   0.9396
   1.000   0.2827   0.01175   0.00427  -0.0031   0.4572   0.9488
   1.250   0.3217   0.01188   0.00432  -0.0053   0.4498   0.9550
   1.500   0.3558   0.01197   0.00431  -0.0067   0.4435   0.9581
   1.750   0.3871   0.01202   0.00432  -0.0075   0.4365   0.9617
   2.000   0.4141   0.01211   0.00433  -0.0075   0.4306   0.9665
   2.250   0.4475   0.01217   0.00435  -0.0088   0.4243   0.9688
   2.500   0.4808   0.01224   0.00437  -0.0101   0.4176   0.9714
   2.750   0.5126   0.01233   0.00441  -0.0111   0.4118   0.9746
   3.000   0.5428   0.01242   0.00450  -0.0118   0.4054   0.9784
   3.500   0.6067   0.01258   0.00458  -0.0139   0.3884   0.9844
   3.750   0.6385   0.01267   0.00462  -0.0150   0.3799   0.9875
   4.000   0.6695   0.01277   0.00472  -0.0159   0.3707   0.9908
   4.250   0.7009   0.01289   0.00483  -0.0169   0.3645   0.9938
   4.500   0.7337   0.01299   0.00494  -0.0182   0.3577   0.9967
   4.750   0.7661   0.01313   0.00508  -0.0195   0.3526   0.9996
   5.000   0.7898   0.01326   0.00526  -0.0189   0.3470   1.0000
   5.250   0.8112   0.01341   0.00543  -0.0179   0.3415   1.0000
   5.500   0.8323   0.01360   0.00560  -0.0169   0.3369   1.0000
   5.750   0.8539   0.01376   0.00583  -0.0159   0.3315   1.0000
   6.000   0.8752   0.01395   0.00607  -0.0148   0.3261   1.0000
   6.500   0.9173   0.01435   0.00655  -0.0127   0.3140   1.0000
   6.750   0.9376   0.01459   0.00677  -0.0115   0.3062   1.0000
   7.000   0.9586   0.01480   0.00706  -0.0104   0.2971   1.0000
   7.250   0.9789   0.01507   0.00733  -0.0093   0.2891   1.0000
   7.500   0.9996   0.01532   0.00764  -0.0082   0.2806   1.0000
   7.750   1.0197   0.01561   0.00796  -0.0070   0.2704   1.0000
   8.000   1.0393   0.01595   0.00831  -0.0058   0.2613   1.0000
   8.250   1.0595   0.01626   0.00869  -0.0047   0.2509   1.0000
   8.500   1.0790   0.01663   0.00910  -0.0035   0.2410   1.0000
   8.750   1.0972   0.01706   0.00954  -0.0022   0.2268   1.0000
   9.000   1.1138   0.01759   0.01006  -0.0008   0.2083   1.0000
   9.250   1.1281   0.01827   0.01066   0.0010   0.1863   1.0000
   9.500   1.1385   0.01919   0.01145   0.0031   0.1565   1.0000
   9.750   1.1411   0.02059   0.01260   0.0059   0.1162   1.0000
  10.000   1.1276   0.02284   0.01446   0.0105   0.0623   1.0000
  10.500   1.0975   0.02696   0.01832   0.0187   0.0186   1.0000
  10.750   1.0973   0.02872   0.02015   0.0201   0.0163   1.0000
  11.000   1.0962   0.03084   0.02235   0.0210   0.0145   1.0000
  11.250   1.0969   0.03300   0.02465   0.0214   0.0134   1.0000
  11.500   1.0973   0.03537   0.02713   0.0215   0.0129   1.0000
  11.750   1.0967   0.03796   0.02983   0.0215   0.0126   1.0000
  12.000   1.0956   0.04069   0.03267   0.0212   0.0120   1.0000
  12.250   1.0919   0.04380   0.03591   0.0208   0.0114   1.0000
  12.500   1.0911   0.04664   0.03885   0.0204   0.0114   1.0000
  12.750   1.0849   0.05018   0.04253   0.0197   0.0112   1.0000
  13.000   1.0788   0.05379   0.04623   0.0189   0.0106   1.0000
  13.250   1.0735   0.05736   0.04993   0.0180   0.0107   1.0000
  13.500   1.0676   0.06109   0.05375   0.0171   0.0104   1.0000
  13.750   1.0606   0.06511   0.05792   0.0159   0.0103   1.0000
  14.000   1.0527   0.06943   0.06236   0.0145   0.0103   1.0000
  14.250   1.0490   0.07325   0.06628   0.0133   0.0100   1.0000
  14.500   1.0421   0.07765   0.07080   0.0118   0.0099   1.0000
  14.750   1.0319   0.08262   0.07587   0.0100   0.0094   1.0000
  15.000   1.0277   0.08676   0.08012   0.0085   0.0094   1.0000
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