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EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EH 3.0/12 (eh3012-il)
Reynolds number: 50,000
Max Cl/Cd: 26.04 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh3012-il-50000-n5.txt
Download as CSV file: xf-eh3012-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4434   0.09980   0.09331  -0.0130   1.0000   0.0609
  -9.250  -0.4439   0.09538   0.08896  -0.0153   1.0000   0.0597
  -9.000  -0.4476   0.09051   0.08417  -0.0184   1.0000   0.0581
  -8.500  -0.4926   0.07791   0.07160  -0.0273   1.0000   0.0535
  -8.250  -0.4937   0.07418   0.06786  -0.0274   1.0000   0.0531
  -8.000  -0.4965   0.07026   0.06389  -0.0274   1.0000   0.0528
  -7.750  -0.4982   0.06644   0.06000  -0.0272   1.0000   0.0525
  -7.500  -0.4988   0.06263   0.05607  -0.0267   1.0000   0.0523
  -7.250  -0.4987   0.05873   0.05200  -0.0258   1.0000   0.0522
  -7.000  -0.4970   0.05498   0.04805  -0.0245   1.0000   0.0521
  -6.750  -0.4939   0.05150   0.04432  -0.0229   1.0000   0.0522
  -6.500  -0.4919   0.04812   0.04062  -0.0207   1.0000   0.0528
  -6.250  -0.4920   0.04537   0.03757  -0.0177   1.0000   0.0539
  -6.000  -0.4633   0.04350   0.03570  -0.0200   0.9765   0.0568
  -5.750  -0.4304   0.04031   0.03204  -0.0225   0.9477   0.0595
  -5.500  -0.3965   0.03675   0.02782  -0.0243   0.9236   0.0615
  -5.250  -0.3627   0.03366   0.02392  -0.0254   0.9007   0.0645
  -5.000  -0.3297   0.03218   0.02238  -0.0267   0.8782   0.0695
  -4.750  -0.2974   0.03039   0.02007  -0.0270   0.8576   0.0756
  -4.500  -0.2679   0.02896   0.01846  -0.0270   0.8369   0.0813
  -4.250  -0.2379   0.02780   0.01695  -0.0267   0.8178   0.0912
  -4.000  -0.2082   0.02679   0.01580  -0.0265   0.8001   0.1026
  -3.750  -0.1784   0.02593   0.01480  -0.0262   0.7832   0.1178
  -3.500  -0.1498   0.02520   0.01394  -0.0259   0.7672   0.1370
  -3.250  -0.1237   0.02450   0.01321  -0.0253   0.7522   0.1585
  -3.000  -0.0988   0.02385   0.01246  -0.0245   0.7378   0.1816
  -2.750  -0.0764   0.02317   0.01183  -0.0234   0.7243   0.2089
  -2.500  -0.0566   0.02246   0.01121  -0.0219   0.7120   0.2467
  -2.250  -0.0207   0.02017   0.01143  -0.0210   0.7005   0.7567
  -2.000   0.0362   0.02116   0.01200  -0.0227   0.6868   0.9007
  -1.750   0.1414   0.02159   0.01175  -0.0352   0.6706   0.9720
  -1.500   0.2103   0.02126   0.01098  -0.0433   0.6563   1.0000
  -1.250   0.2314   0.02130   0.01079  -0.0424   0.6453   1.0000
  -1.000   0.2524   0.02133   0.01060  -0.0414   0.6358   1.0000
  -0.750   0.2740   0.02142   0.01055  -0.0407   0.6246   1.0000
  -0.500   0.2953   0.02151   0.01048  -0.0398   0.6149   1.0000
  -0.250   0.3164   0.02160   0.01041  -0.0389   0.6056   1.0000
   0.000   0.3377   0.02176   0.01045  -0.0381   0.5959   1.0000
   0.250   0.3586   0.02187   0.01039  -0.0369   0.5880   1.0000
   0.500   0.3800   0.02209   0.01056  -0.0362   0.5781   1.0000
   0.750   0.4014   0.02224   0.01056  -0.0352   0.5708   1.0000
   1.000   0.4225   0.02251   0.01082  -0.0345   0.5614   1.0000
   1.250   0.4435   0.02271   0.01088  -0.0333   0.5541   1.0000
   1.500   0.4642   0.02302   0.01117  -0.0325   0.5452   1.0000
   1.750   0.4852   0.02324   0.01127  -0.0313   0.5387   1.0000
   2.000   0.5054   0.02363   0.01167  -0.0305   0.5298   1.0000
   2.250   0.5264   0.02383   0.01176  -0.0292   0.5237   1.0000
   2.500   0.5460   0.02432   0.01231  -0.0284   0.5149   1.0000
   2.750   0.5668   0.02457   0.01249  -0.0271   0.5088   1.0000
   3.000   0.5860   0.02510   0.01307  -0.0262   0.5004   1.0000
   3.250   0.6065   0.02541   0.01333  -0.0249   0.4941   1.0000
   3.500   0.6255   0.02595   0.01391  -0.0239   0.4867   1.0000
   3.750   0.6453   0.02637   0.01433  -0.0227   0.4799   1.0000
   4.000   0.6650   0.02681   0.01481  -0.0215   0.4735   1.0000
   4.250   0.6833   0.02744   0.01550  -0.0203   0.4661   1.0000
   4.500   0.7049   0.02771   0.01572  -0.0191   0.4610   1.0000
   4.750   0.7207   0.02859   0.01674  -0.0179   0.4528   1.0000
   5.000   0.7413   0.02898   0.01713  -0.0167   0.4471   1.0000
   5.250   0.7583   0.02976   0.01804  -0.0155   0.4403   1.0000
   5.500   0.7763   0.03043   0.01878  -0.0143   0.4337   1.0000
   5.750   0.7990   0.03068   0.01900  -0.0132   0.4290   1.0000
   6.000   0.8103   0.03197   0.02050  -0.0118   0.4207   1.0000
   6.250   0.8317   0.03236   0.02094  -0.0106   0.4155   1.0000
   6.500   0.8444   0.03352   0.02226  -0.0092   0.4084   1.0000
   6.750   0.8614   0.03429   0.02313  -0.0079   0.4021   1.0000
   7.000   0.8853   0.03453   0.02337  -0.0070   0.3978   1.0000
   7.250   0.8886   0.03646   0.02555  -0.0052   0.3893   1.0000
   7.500   0.9112   0.03678   0.02596  -0.0042   0.3843   1.0000
   7.750   0.9159   0.03860   0.02796  -0.0025   0.3770   1.0000
   8.000   0.9304   0.03959   0.02908  -0.0012   0.3710   1.0000
   8.250   0.9573   0.03964   0.02917  -0.0004   0.3667   1.0000
   8.500   0.9425   0.04292   0.03270   0.0019   0.3577   1.0000
   8.750   0.9681   0.04305   0.03293   0.0028   0.3533   1.0000
   9.000   0.9432   0.04715   0.03718   0.0051   0.3446   1.0000
   9.250   0.9599   0.04789   0.03806   0.0063   0.3393   1.0000
   9.500   0.9059   0.05445   0.04458   0.0083   0.3296   1.0000
   9.750   0.9158   0.05588   0.04614   0.0092   0.3241   1.0000
  10.000   0.9447   0.05545   0.04587   0.0105   0.3204   1.0000
  10.250   0.8860   0.06493   0.05528   0.0082   0.3080   1.0000
  10.750   0.8687   0.07345   0.06391   0.0067   0.2926   1.0000
  11.000   0.8355   0.08117   0.07159   0.0041   0.2818   1.0000
  11.250   0.8550   0.08172   0.07230   0.0051   0.2778   1.0000
  12.250   0.8358   0.09783   0.08869   0.0013   0.2497   1.0000
  13.250   0.8296   0.11283   0.10407  -0.0027   0.2232   1.0000
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