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EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 330 AIRFOIL (e330-il)
Reynolds number: 1,000,000
Max Cl/Cd: 89.57 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e330-il-1000000.txt
Download as CSV file: xf-e330-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5438   0.08533   0.08387   0.0016   1.0000   0.0072
  -8.750  -0.5559   0.07978   0.07832  -0.0033   1.0000   0.0072
  -8.500  -0.5695   0.07542   0.07395  -0.0049   1.0000   0.0070
  -8.250  -0.5837   0.07173   0.07022  -0.0042   1.0000   0.0070
  -8.000  -0.5949   0.06817   0.06661  -0.0026   1.0000   0.0070
  -7.750  -0.5996   0.06387   0.06222  -0.0015   1.0000   0.0073
  -7.500  -0.6001   0.05983   0.05809  -0.0002   1.0000   0.0074
  -6.750  -0.5745   0.04823   0.04548   0.0044   0.7786   0.0078
  -6.500  -0.5660   0.04476   0.04175   0.0068   0.7522   0.0078
  -6.250  -0.5569   0.04116   0.03788   0.0095   0.7296   0.0078
  -6.000  -0.5473   0.03758   0.03400   0.0124   0.7113   0.0078
  -5.750  -0.5532   0.03108   0.02703   0.0172   0.6971   0.0083
  -5.500  -0.5376   0.02936   0.02512   0.0189   0.6796   0.0085
  -5.250  -0.5202   0.02768   0.02324   0.0206   0.6632   0.0087
  -5.000  -0.5018   0.02596   0.02129   0.0223   0.6473   0.0090
  -4.750  -0.4821   0.02415   0.01924   0.0240   0.6324   0.0094
  -4.500  -0.4608   0.02238   0.01719   0.0257   0.6185   0.0101
  -4.250  -0.4340   0.02224   0.01682   0.0269   0.6043   0.0114
  -4.000  -0.4113   0.02133   0.01562   0.0283   0.5910   0.0115
  -3.750  -0.3880   0.01519   0.00889   0.0306   0.5808   0.0085
  -3.500  -0.3602   0.01254   0.00590   0.0319   0.5691   0.0054
  -3.250  -0.3353   0.01187   0.00513   0.0327   0.5573   0.0054
  -3.000  -0.3112   0.01127   0.00443   0.0336   0.5452   0.0054
  -2.750  -0.2881   0.01063   0.00368   0.0348   0.5340   0.0057
  -2.500  -0.2633   0.01027   0.00326   0.0356   0.5227   0.0062
  -2.250  -0.2379   0.01002   0.00295   0.0362   0.5121   0.0071
  -2.000  -0.2123   0.00980   0.00266   0.0368   0.5015   0.0076
  -1.750  -0.1871   0.00953   0.00232   0.0375   0.4911   0.0097
  -1.500  -0.1615   0.00931   0.00208   0.0381   0.4817   0.0150
  -1.250  -0.1392   0.00882   0.00187   0.0392   0.4729   0.0940
  -1.000  -0.1149   0.00854   0.00178   0.0399   0.4635   0.1639
  -0.750  -0.1034   0.00735   0.00153   0.0428   0.4563   0.4404
  -0.500  -0.1115   0.00571   0.00123   0.0503   0.4507   0.7911
  -0.250  -0.0919   0.00577   0.00158   0.0528   0.4433   0.9018
   0.000  -0.0651   0.00601   0.00179   0.0536   0.4350   0.9177
   0.250  -0.0389   0.00633   0.00206   0.0544   0.4274   0.9300
   0.500  -0.0018   0.00668   0.00235   0.0529   0.4190   0.9349
   0.750   0.0310   0.00694   0.00255   0.0521   0.4118   0.9392
   1.000   0.0577   0.00715   0.00269   0.0526   0.4043   0.9446
   1.250   0.0938   0.00731   0.00280   0.0510   0.3972   0.9458
   1.500   0.1296   0.00747   0.00289   0.0493   0.3900   0.9467
   1.750   0.1650   0.00760   0.00297   0.0477   0.3833   0.9475
   2.000   0.1986   0.00770   0.00302   0.0465   0.3764   0.9482
   2.250   0.2324   0.00780   0.00307   0.0452   0.3702   0.9489
   2.500   0.2644   0.00787   0.00311   0.0442   0.3639   0.9498
   2.750   0.2949   0.00796   0.00315   0.0436   0.3578   0.9508
   3.000   0.3247   0.00800   0.00318   0.0431   0.3523   0.9520
   3.250   0.3509   0.00808   0.00322   0.0434   0.3463   0.9537
   3.500   0.3563   0.00806   0.00321   0.0483   0.3425   0.9585
   3.750   0.3930   0.00815   0.00328   0.0463   0.3361   0.9590
   4.000   0.4250   0.00824   0.00333   0.0452   0.3298   0.9593
   4.250   0.4596   0.00830   0.00339   0.0437   0.3242   0.9598
   4.500   0.4936   0.00841   0.00348   0.0422   0.3177   0.9603
   4.750   0.5271   0.00850   0.00356   0.0409   0.3120   0.9609
   5.000   0.5600   0.00859   0.00365   0.0396   0.3056   0.9616
   5.250   0.5931   0.00871   0.00376   0.0383   0.2992   0.9625
   5.500   0.6223   0.00878   0.00383   0.0379   0.2929   0.9632
   5.750   0.6500   0.00887   0.00391   0.0377   0.2861   0.9639
   6.000   0.6773   0.00893   0.00399   0.0376   0.2793   0.9647
   6.250   0.7035   0.00904   0.00409   0.0377   0.2724   0.9657
   6.500   0.7294   0.00912   0.00418   0.0380   0.2655   0.9667
   6.750   0.7537   0.00925   0.00430   0.0385   0.2577   0.9682
   7.000   0.7726   0.00933   0.00441   0.0402   0.2512   0.9701
   7.250   0.7862   0.00945   0.00452   0.0430   0.2440   0.9724
   7.500   0.8154   0.00957   0.00464   0.0424   0.2344   0.9727
   7.750   0.8445   0.00971   0.00479   0.0418   0.2247   0.9731
   8.000   0.8731   0.00991   0.00497   0.0413   0.2125   0.9736
   8.250   0.9013   0.01013   0.00518   0.0408   0.2002   0.9741
   8.500   0.9297   0.01039   0.00541   0.0402   0.1874   0.9747
   8.750   0.9575   0.01069   0.00568   0.0397   0.1726   0.9753
   9.000   0.9833   0.01112   0.00603   0.0395   0.1525   0.9761
   9.250   1.0084   0.01154   0.00639   0.0394   0.1355   0.9770
   9.500   1.0324   0.01200   0.00681   0.0395   0.1180   0.9781
   9.750   1.0554   0.01250   0.00725   0.0398   0.1027   0.9793
  10.000   1.0758   0.01308   0.00775   0.0405   0.0864   0.9809
  10.250   1.0933   0.01358   0.00823   0.0419   0.0752   0.9830
  10.500   1.1093   0.01415   0.00875   0.0434   0.0628   0.9850
  10.750   1.1354   0.01480   0.00937   0.0427   0.0509   0.9857
  11.000   1.1604   0.01555   0.01007   0.0420   0.0390   0.9865
  11.250   1.1842   0.01630   0.01080   0.0415   0.0307   0.9875
  11.500   1.2065   0.01710   0.01158   0.0413   0.0239   0.9887
  11.750   1.2295   0.01772   0.01225   0.0410   0.0211   0.9899
  12.000   1.2491   0.01857   0.01311   0.0411   0.0170   0.9917
  12.250   1.2683   0.01932   0.01391   0.0414   0.0149   0.9936
  12.500   1.2861   0.02036   0.01497   0.0414   0.0119   0.9953
  12.750   1.3083   0.02126   0.01595   0.0405   0.0106   0.9966
  13.000   1.3234   0.02239   0.01713   0.0404   0.0091   0.9988
  13.250   1.3231   0.02366   0.01848   0.0423   0.0080   1.0000
  13.500   1.3024   0.02502   0.01993   0.0474   0.0079   1.0000
  13.750   1.2896   0.02675   0.02173   0.0506   0.0076   1.0000
  14.000   1.2812   0.02896   0.02403   0.0521   0.0072   1.0000
  14.250   1.2754   0.03151   0.02665   0.0527   0.0066   1.0000
  14.500   1.2685   0.03451   0.02972   0.0526   0.0061   1.0000
  14.750   1.2604   0.03787   0.03315   0.0522   0.0052   1.0000
  15.000   1.2529   0.04131   0.03670   0.0515   0.0053   1.0000
  15.250   1.2451   0.04486   0.04033   0.0507   0.0044   1.0000
  15.500   1.2385   0.04835   0.04390   0.0499   0.0045   1.0000
  15.750   1.2298   0.05212   0.04777   0.0488   0.0044   1.0000
  16.000   1.2138   0.05690   0.05264   0.0474   0.0039   1.0000
  16.250   1.1996   0.06161   0.05744   0.0458   0.0036   1.0000
  16.500   1.1894   0.06598   0.06188   0.0443   0.0031   1.0000
  16.750   1.1769   0.07079   0.06680   0.0425   0.0032   1.0000
  17.000   1.1675   0.07529   0.07138   0.0408   0.0028   1.0000
  17.250   1.1572   0.07998   0.07616   0.0390   0.0029   1.0000
  17.500   1.1437   0.08525   0.08153   0.0369   0.0028   1.0000
  17.750   1.1306   0.09058   0.08693   0.0348   0.0024   1.0000
  18.000   1.1212   0.09535   0.09180   0.0329   0.0027   1.0000
  18.250   1.1057   0.10122   0.09773   0.0304   0.0022   1.0000
  18.500   1.0881   0.10760   0.10420   0.0276   0.0019   1.0000
  18.750   1.0893   0.11078   0.10746   0.0263   0.0023   1.0000
  19.000   1.0697   0.11769   0.11446   0.0233   0.0021   1.0000
  19.250   1.0612   0.12272   0.11957   0.0210   0.0021   1.0000
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