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EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 340 AIRFOIL (e340-il)
Reynolds number: 500,000
Max Cl/Cd: 74.34 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e340-il-500000-n5.txt
Download as CSV file: xf-e340-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 340 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5889   0.08829   0.08614   0.0032   0.8742   0.0064
 -10.000  -0.6073   0.08034   0.07793  -0.0036   0.8082   0.0063
  -9.500  -0.6447   0.06917   0.06637  -0.0073   0.7524   0.0062
  -9.250  -0.6635   0.06443   0.06143  -0.0059   0.7325   0.0062
  -9.000  -0.6790   0.06002   0.05682  -0.0034   0.7151   0.0061
  -8.750  -0.6904   0.05529   0.05184  -0.0007   0.7001   0.0061
  -8.500  -0.6978   0.05024   0.04651   0.0023   0.6864   0.0061
  -8.250  -0.7032   0.04467   0.04058   0.0058   0.6740   0.0061
  -8.000  -0.7138   0.03663   0.03196   0.0110   0.6650   0.0061
  -7.750  -0.7138   0.03078   0.02542   0.0153   0.6540   0.0063
  -7.500  -0.7008   0.02794   0.02210   0.0178   0.6399   0.0063
  -7.250  -0.6840   0.02571   0.01948   0.0196   0.6258   0.0063
  -7.000  -0.6644   0.02382   0.01725   0.0211   0.6122   0.0063
  -6.750  -0.6424   0.02231   0.01544   0.0222   0.5989   0.0063
  -6.500  -0.6189   0.02098   0.01384   0.0230   0.5865   0.0063
  -6.250  -0.5943   0.01984   0.01247   0.0237   0.5747   0.0063
  -6.000  -0.5690   0.01885   0.01129   0.0242   0.5637   0.0063
  -5.750  -0.5435   0.01800   0.01027   0.0247   0.5529   0.0064
  -5.500  -0.5179   0.01724   0.00936   0.0252   0.5415   0.0064
  -5.250  -0.4928   0.01648   0.00850   0.0258   0.5308   0.0065
  -5.000  -0.4682   0.01576   0.00768   0.0264   0.5211   0.0066
  -4.750  -0.4436   0.01518   0.00703   0.0271   0.5118   0.0067
  -4.500  -0.4189   0.01470   0.00647   0.0277   0.5033   0.0069
  -4.250  -0.3941   0.01427   0.00599   0.0283   0.4946   0.0071
  -4.000  -0.3691   0.01391   0.00556   0.0289   0.4865   0.0074
  -3.750  -0.3440   0.01357   0.00515   0.0295   0.4776   0.0078
  -3.500  -0.3188   0.01327   0.00478   0.0301   0.4698   0.0083
  -3.250  -0.2935   0.01298   0.00443   0.0307   0.4619   0.0089
  -3.000  -0.2681   0.01272   0.00412   0.0312   0.4551   0.0101
  -2.750  -0.2424   0.01249   0.00385   0.0317   0.4485   0.0117
  -2.500  -0.2170   0.01228   0.00361   0.0322   0.4417   0.0147
  -2.250  -0.1919   0.01205   0.00339   0.0327   0.4355   0.0237
  -2.000  -0.1674   0.01176   0.00321   0.0334   0.4288   0.0498
  -1.750  -0.1436   0.01147   0.00305   0.0341   0.4227   0.0916
  -1.500  -0.1205   0.01109   0.00290   0.0349   0.4177   0.1571
  -1.250  -0.1182   0.00948   0.00253   0.0393   0.4135   0.4807
  -1.000  -0.1131   0.00854   0.00316   0.0450   0.4093   0.8540
  -0.750  -0.0927   0.00888   0.00343   0.0471   0.4048   0.8776
  -0.500  -0.0655   0.00923   0.00372   0.0477   0.3996   0.8884
  -0.250  -0.0437   0.00951   0.00392   0.0493   0.3944   0.8991
   0.000   0.0021   0.01026   0.00458   0.0464   0.3889   0.9038
   0.250   0.0352   0.01063   0.00489   0.0458   0.3843   0.9096
   0.500   0.0557   0.01066   0.00485   0.0474   0.3799   0.9144
   0.750   0.0859   0.01073   0.00483   0.0469   0.3752   0.9151
   1.000   0.1158   0.01077   0.00482   0.0464   0.3712   0.9158
   1.250   0.1453   0.01081   0.00481   0.0460   0.3672   0.9165
   1.500   0.1745   0.01086   0.00480   0.0457   0.3633   0.9173
   1.750   0.2029   0.01091   0.00480   0.0455   0.3597   0.9183
   2.000   0.2310   0.01096   0.00480   0.0454   0.3564   0.9193
   2.250   0.2580   0.01098   0.00480   0.0455   0.3527   0.9206
   2.500   0.2837   0.01100   0.00478   0.0459   0.3488   0.9220
   2.750   0.3068   0.01101   0.00476   0.0467   0.3453   0.9240
   3.000   0.3173   0.01092   0.00463   0.0501   0.3423   0.9281
   3.250   0.3459   0.01095   0.00465   0.0498   0.3392   0.9285
   3.500   0.3740   0.01098   0.00468   0.0497   0.3362   0.9290
   3.750   0.4018   0.01102   0.00472   0.0495   0.3330   0.9295
   4.000   0.4298   0.01110   0.00477   0.0493   0.3298   0.9301
   4.250   0.4574   0.01120   0.00483   0.0492   0.3264   0.9308
   4.500   0.4848   0.01124   0.00489   0.0491   0.3234   0.9314
   4.750   0.5116   0.01128   0.00496   0.0492   0.3200   0.9321
   5.000   0.5379   0.01134   0.00501   0.0493   0.3164   0.9328
   5.250   0.5635   0.01142   0.00508   0.0495   0.3134   0.9337
   5.500   0.5886   0.01151   0.00517   0.0499   0.3104   0.9346
   5.750   0.6142   0.01156   0.00526   0.0501   0.3074   0.9358
   6.000   0.6384   0.01161   0.00533   0.0507   0.3039   0.9370
   6.250   0.6614   0.01166   0.00539   0.0514   0.3005   0.9383
   6.500   0.6831   0.01172   0.00546   0.0524   0.2969   0.9397
   6.750   0.7050   0.01177   0.00552   0.0533   0.2935   0.9411
   7.000   0.7298   0.01182   0.00562   0.0536   0.2897   0.9419
   7.250   0.7562   0.01193   0.00576   0.0536   0.2855   0.9424
   7.500   0.7821   0.01207   0.00590   0.0537   0.2812   0.9430
   7.750   0.8086   0.01219   0.00607   0.0536   0.2769   0.9436
   8.000   0.8347   0.01231   0.00624   0.0536   0.2716   0.9444
   8.250   0.8596   0.01247   0.00641   0.0538   0.2668   0.9451
   8.500   0.8847   0.01260   0.00660   0.0540   0.2623   0.9459
   8.750   0.9094   0.01274   0.00678   0.0542   0.2562   0.9467
   9.000   0.9329   0.01294   0.00698   0.0546   0.2498   0.9477
   9.250   0.9570   0.01309   0.00719   0.0549   0.2430   0.9487
   9.500   0.9794   0.01332   0.00743   0.0554   0.2362   0.9499
   9.750   1.0024   0.01352   0.00767   0.0558   0.2282   0.9511
  10.000   1.0240   0.01379   0.00794   0.0564   0.2196   0.9524
  10.250   1.0459   0.01407   0.00825   0.0569   0.2101   0.9536
  10.500   1.0680   0.01441   0.00861   0.0573   0.2007   0.9544
  10.750   1.0884   0.01483   0.00904   0.0579   0.1896   0.9555
  11.000   1.1075   0.01531   0.00952   0.0586   0.1784   0.9569
  11.250   1.1256   0.01583   0.01004   0.0595   0.1668   0.9584
  11.500   1.1419   0.01641   0.01062   0.0604   0.1542   0.9601
  11.750   1.1558   0.01711   0.01130   0.0616   0.1410   0.9622
  12.000   1.1659   0.01786   0.01204   0.0633   0.1288   0.9644
  12.250   1.1755   0.01876   0.01296   0.0648   0.1180   0.9665
  12.500   1.1834   0.01987   0.01409   0.0660   0.1078   0.9691
  12.750   1.1891   0.02128   0.01552   0.0667   0.0989   0.9722
  13.000   1.1952   0.02302   0.01730   0.0666   0.0906   0.9747
  13.250   1.2019   0.02504   0.01938   0.0658   0.0833   0.9773
  13.500   1.2050   0.02762   0.02201   0.0645   0.0767   0.9807
  13.750   1.2083   0.03022   0.02468   0.0632   0.0709   0.9854
  14.000   1.2069   0.03335   0.02787   0.0618   0.0662   0.9901
  14.250   1.2072   0.03644   0.03104   0.0603   0.0620   0.9941
  14.750   1.2033   0.04372   0.03847   0.0558   0.0548   0.9971
  15.000   1.1983   0.04761   0.04245   0.0536   0.0515   0.9983
  15.500   1.1768   0.05516   0.05013   0.0518   0.0468   1.0000
  15.750   1.1673   0.05905   0.05408   0.0507   0.0444   1.0000
  16.000   1.1568   0.06326   0.05835   0.0494   0.0420   1.0000
  16.250   1.1494   0.06716   0.06232   0.0481   0.0398   1.0000
  16.500   1.1422   0.07115   0.06636   0.0467   0.0373   1.0000
  16.750   1.1326   0.07552   0.07078   0.0451   0.0351   1.0000
  17.000   1.1264   0.07950   0.07483   0.0436   0.0333   1.0000
  17.250   1.1199   0.08357   0.07896   0.0421   0.0310   1.0000
  17.750   1.1061   0.09197   0.08747   0.0388   0.0273   1.0000
  18.000   1.0994   0.09622   0.09176   0.0371   0.0253   1.0000
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