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EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 330 AIRFOIL (e330-il)
Reynolds number: 500,000
Max Cl/Cd: 71.86 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e330-il-500000-n5.txt
Download as CSV file: xf-e330-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 330 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4557   0.08406   0.08217   0.0049   1.0000   0.0085
  -9.000  -0.4629   0.07844   0.07656   0.0023   1.0000   0.0085
  -8.750  -0.4740   0.07175   0.06972  -0.0020   0.8634   0.0084
  -8.500  -0.5680   0.07357   0.07144  -0.0061   1.0000   0.0078
  -8.250  -0.5790   0.06995   0.06778  -0.0050   1.0000   0.0078
  -8.000  -0.5835   0.06594   0.06367  -0.0045   0.9379   0.0078
  -7.750  -0.5838   0.06187   0.05917  -0.0038   0.8258   0.0079
  -7.500  -0.5857   0.05851   0.05554  -0.0016   0.7849   0.0078
  -7.250  -0.5849   0.05494   0.05173   0.0006   0.7571   0.0078
  -7.000  -0.5823   0.05119   0.04772   0.0029   0.7350   0.0078
  -6.750  -0.5936   0.04405   0.04026   0.0074   0.7204   0.0051
  -6.500  -0.5878   0.04141   0.03736   0.0096   0.7013   0.0049
  -6.250  -0.5792   0.03781   0.03346   0.0123   0.6855   0.0048
  -6.000  -0.5691   0.03395   0.02924   0.0152   0.6701   0.0046
  -5.750  -0.5567   0.03019   0.02509   0.0182   0.6566   0.0044
  -5.500  -0.5430   0.02600   0.02040   0.0215   0.6438   0.0043
  -5.250  -0.5251   0.02245   0.01634   0.0241   0.6314   0.0041
  -5.000  -0.5030   0.01956   0.01294   0.0259   0.6186   0.0040
  -4.750  -0.4780   0.01775   0.01075   0.0269   0.6048   0.0040
  -4.500  -0.4524   0.01645   0.00919   0.0277   0.5917   0.0041
  -4.250  -0.4268   0.01539   0.00792   0.0284   0.5792   0.0042
  -4.000  -0.4017   0.01462   0.00699   0.0291   0.5670   0.0043
  -3.750  -0.3771   0.01394   0.00617   0.0300   0.5548   0.0044
  -3.500  -0.3527   0.01337   0.00548   0.0308   0.5435   0.0047
  -3.250  -0.3282   0.01292   0.00492   0.0316   0.5327   0.0050
  -3.000  -0.3040   0.01245   0.00437   0.0325   0.5221   0.0054
  -2.750  -0.2792   0.01211   0.00396   0.0332   0.5112   0.0062
  -2.500  -0.2541   0.01185   0.00362   0.0338   0.5014   0.0069
  -2.250  -0.2286   0.01163   0.00334   0.0344   0.4917   0.0081
  -2.000  -0.2035   0.01139   0.00305   0.0350   0.4824   0.0100
  -1.750  -0.1783   0.01116   0.00277   0.0357   0.4733   0.0147
  -1.500  -0.1533   0.01091   0.00255   0.0363   0.4644   0.0318
  -1.250  -0.1301   0.01051   0.00237   0.0372   0.4563   0.0943
  -1.000  -0.1068   0.01015   0.00224   0.0380   0.4482   0.1725
  -0.750  -0.1075   0.00828   0.00187   0.0431   0.4426   0.5760
  -0.500  -0.0908   0.00752   0.00228   0.0464   0.4356   0.8797
  -0.250  -0.0650   0.00784   0.00253   0.0475   0.4283   0.9057
   0.000  -0.0385   0.00807   0.00268   0.0482   0.4203   0.9171
   0.250  -0.0010   0.00842   0.00292   0.0465   0.4128   0.9237
   0.500   0.0234   0.00857   0.00300   0.0475   0.4060   0.9305
   0.750   0.0569   0.00870   0.00304   0.0464   0.3990   0.9318
   1.000   0.0900   0.00882   0.00308   0.0453   0.3919   0.9331
   1.250   0.1221   0.00894   0.00313   0.0445   0.3857   0.9346
   1.500   0.1519   0.00900   0.00314   0.0440   0.3791   0.9360
   1.750   0.1802   0.00909   0.00315   0.0439   0.3729   0.9378
   2.000   0.2051   0.00912   0.00316   0.0446   0.3674   0.9402
   2.250   0.2216   0.00913   0.00313   0.0470   0.3622   0.9441
   2.500   0.2549   0.00924   0.00319   0.0458   0.3561   0.9449
   2.750   0.2881   0.00934   0.00327   0.0446   0.3501   0.9457
   3.250   0.3504   0.00951   0.00338   0.0430   0.3387   0.9471
   3.500   0.3822   0.00962   0.00346   0.0420   0.3327   0.9480
   3.750   0.4158   0.00975   0.00357   0.0407   0.3272   0.9494
   4.000   0.4470   0.00986   0.00367   0.0399   0.3209   0.9509
   4.250   0.4741   0.00997   0.00375   0.0399   0.3155   0.9525
   4.500   0.4983   0.01002   0.00383   0.0406   0.3100   0.9540
   4.750   0.5148   0.01007   0.00388   0.0429   0.3048   0.9567
   5.000   0.5370   0.01015   0.00395   0.0440   0.2994   0.9585
   5.250   0.5669   0.01023   0.00405   0.0433   0.2932   0.9589
   5.500   0.5959   0.01036   0.00417   0.0428   0.2866   0.9594
   5.750   0.6250   0.01045   0.00429   0.0424   0.2802   0.9598
   6.000   0.6533   0.01059   0.00442   0.0420   0.2731   0.9604
   6.250   0.6818   0.01070   0.00457   0.0416   0.2656   0.9610
   6.500   0.7097   0.01085   0.00473   0.0414   0.2577   0.9616
   6.750   0.7373   0.01100   0.00489   0.0411   0.2492   0.9624
   7.000   0.7645   0.01117   0.00508   0.0409   0.2405   0.9632
   7.250   0.7914   0.01138   0.00530   0.0408   0.2312   0.9642
   7.500   0.8178   0.01157   0.00551   0.0408   0.2214   0.9653
   7.750   0.8424   0.01180   0.00574   0.0411   0.2102   0.9666
   8.000   0.8655   0.01205   0.00600   0.0416   0.1989   0.9681
   8.250   0.8853   0.01232   0.00628   0.0429   0.1872   0.9701
   8.500   0.9028   0.01262   0.00656   0.0446   0.1746   0.9723
   8.750   0.9298   0.01302   0.00694   0.0441   0.1577   0.9728
   9.000   0.9561   0.01348   0.00737   0.0437   0.1415   0.9735
   9.250   0.9821   0.01398   0.00785   0.0433   0.1264   0.9743
   9.500   1.0073   0.01457   0.00842   0.0430   0.1102   0.9753
   9.750   1.0313   0.01519   0.00901   0.0428   0.0941   0.9765
  10.000   1.0534   0.01587   0.00965   0.0429   0.0792   0.9780
  10.250   1.0745   0.01652   0.01030   0.0432   0.0679   0.9797
  10.500   1.0939   0.01717   0.01096   0.0439   0.0592   0.9817
  10.750   1.1081   0.01786   0.01165   0.0455   0.0515   0.9845
  11.000   1.1310   0.01865   0.01246   0.0451   0.0434   0.9855
  11.250   1.1535   0.01945   0.01333   0.0447   0.0371   0.9867
  11.500   1.1737   0.02040   0.01431   0.0444   0.0315   0.9884
  11.750   1.1930   0.02136   0.01533   0.0442   0.0268   0.9905
  12.000   1.2091   0.02250   0.01651   0.0443   0.0225   0.9934
  12.250   1.2215   0.02367   0.01775   0.0446   0.0193   0.9962
  12.500   1.2327   0.02523   0.01940   0.0440   0.0166   0.9992
  12.750   1.2265   0.02683   0.02109   0.0461   0.0152   1.0000
  13.000   1.2149   0.02869   0.02304   0.0488   0.0148   1.0000
  13.250   1.2058   0.03099   0.02541   0.0503   0.0138   1.0000
  13.500   1.1979   0.03368   0.02817   0.0509   0.0129   1.0000
  13.750   1.1903   0.03667   0.03124   0.0510   0.0120   1.0000
  14.000   1.1845   0.03969   0.03437   0.0509   0.0114   1.0000
  14.250   1.1785   0.04285   0.03764   0.0504   0.0108   1.0000
  14.500   1.1703   0.04638   0.04124   0.0498   0.0099   1.0000
  14.750   1.1590   0.05035   0.04526   0.0489   0.0087   1.0000
  15.000   1.1522   0.05387   0.04892   0.0480   0.0092   1.0000
  15.250   1.1394   0.05821   0.05331   0.0468   0.0079   1.0000
  15.500   1.1313   0.06205   0.05725   0.0457   0.0076   1.0000
  15.750   1.1231   0.06608   0.06136   0.0444   0.0072   1.0000
  16.000   1.1139   0.07039   0.06578   0.0430   0.0071   1.0000
  16.250   1.1049   0.07478   0.07026   0.0414   0.0067   1.0000
  16.500   1.0934   0.07958   0.07510   0.0395   0.0056   1.0000
  16.750   1.0862   0.08390   0.07953   0.0380   0.0059   1.0000
  17.000   1.0759   0.08876   0.08445   0.0360   0.0050   1.0000
  17.250   1.0669   0.09353   0.08932   0.0341   0.0051   1.0000
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