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EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 340 AIRFOIL (e340-il)
Reynolds number: 1,000,000
Max Cl/Cd: 94.19 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e340-il-1000000.txt
Download as CSV file: xf-e340-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5680   0.08503   0.08362  -0.0018   1.0000   0.0087
  -9.750  -0.5828   0.07690   0.07544  -0.0086   1.0000   0.0087
  -9.500  -0.6001   0.07074   0.06919  -0.0107   1.0000   0.0087
  -9.250  -0.6246   0.06712   0.06510  -0.0074   0.8212   0.0087
  -9.000  -0.6615   0.06058   0.05828  -0.0045   0.7883   0.0088
  -8.750  -0.6760   0.05721   0.05468  -0.0015   0.7587   0.0089
  -8.500  -0.6785   0.05424   0.05151   0.0006   0.7341   0.0090
  -5.750  -0.5631   0.01850   0.01213   0.0275   0.5794   0.0089
  -5.500  -0.5371   0.01775   0.01122   0.0281   0.5678   0.0088
  -5.250  -0.5105   0.01673   0.01004   0.0284   0.5562   0.0088
  -5.000  -0.4836   0.01602   0.00922   0.0288   0.5450   0.0088
  -4.750  -0.4563   0.01494   0.00807   0.0290   0.5343   0.0086
  -4.250  -0.4047   0.01326   0.00621   0.0300   0.5137   0.0084
  -4.000  -0.3798   0.01270   0.00557   0.0307   0.5044   0.0084
  -3.750  -0.3549   0.01222   0.00503   0.0314   0.4954   0.0084
  -3.500  -0.3300   0.01182   0.00456   0.0321   0.4869   0.0085
  -3.250  -0.3047   0.01148   0.00416   0.0327   0.4781   0.0086
  -3.000  -0.2801   0.01109   0.00370   0.0334   0.4699   0.0089
  -2.750  -0.2547   0.01077   0.00335   0.0340   0.4619   0.0095
  -2.500  -0.2286   0.01058   0.00310   0.0344   0.4543   0.0107
  -2.250  -0.2030   0.01032   0.00282   0.0350   0.4475   0.0145
  -2.000  -0.1789   0.00998   0.00258   0.0358   0.4404   0.0420
  -1.750  -0.1544   0.00968   0.00244   0.0364   0.4344   0.0835
  -1.500  -0.1304   0.00938   0.00231   0.0371   0.4278   0.1396
  -1.250  -0.1141   0.00859   0.00211   0.0391   0.4218   0.3145
  -1.000  -0.1171   0.00707   0.00176   0.0449   0.4180   0.6221
  -0.750  -0.1169   0.00632   0.00196   0.0513   0.4138   0.8610
  -0.500  -0.0917   0.00689   0.00252   0.0527   0.4079   0.8933
  -0.250  -0.0611   0.00744   0.00304   0.0528   0.4027   0.9038
   0.000  -0.0312   0.00784   0.00340   0.0529   0.3972   0.9103
   0.250  -0.0004   0.00828   0.00376   0.0527   0.3914   0.9156
   0.500   0.0438   0.00893   0.00437   0.0501   0.3867   0.9181
   0.750   0.0892   0.00942   0.00480   0.0469   0.3816   0.9198
   1.000   0.1258   0.00965   0.00495   0.0452   0.3767   0.9214
   1.250   0.1496   0.00967   0.00494   0.0460   0.3727   0.9239
   1.500   0.1593   0.00950   0.00475   0.0496   0.3697   0.9290
   1.750   0.1898   0.00952   0.00473   0.0491   0.3654   0.9295
   2.000   0.2198   0.00956   0.00472   0.0485   0.3610   0.9300
   2.250   0.2498   0.00962   0.00473   0.0480   0.3570   0.9305
   2.500   0.2803   0.00963   0.00474   0.0474   0.3541   0.9311
   2.750   0.3107   0.00966   0.00475   0.0468   0.3507   0.9316
   3.000   0.3406   0.00971   0.00476   0.0462   0.3473   0.9322
   3.250   0.3695   0.00979   0.00480   0.0459   0.3432   0.9329
   3.500   0.3975   0.00980   0.00481   0.0457   0.3402   0.9337
   3.750   0.4255   0.00981   0.00482   0.0456   0.3373   0.9346
   4.000   0.4509   0.00982   0.00482   0.0460   0.3339   0.9359
   4.250   0.4712   0.00982   0.00480   0.0474   0.3308   0.9376
   4.500   0.4743   0.00967   0.00463   0.0523   0.3281   0.9420
   4.750   0.5018   0.00969   0.00465   0.0522   0.3252   0.9424
   5.000   0.5306   0.00969   0.00467   0.0518   0.3225   0.9429
   5.250   0.5588   0.00972   0.00471   0.0516   0.3194   0.9434
   5.500   0.5859   0.00976   0.00475   0.0515   0.3161   0.9439
   5.750   0.6121   0.00984   0.00481   0.0516   0.3118   0.9444
   6.000   0.6388   0.00987   0.00485   0.0517   0.3088   0.9450
   6.250   0.6656   0.00989   0.00490   0.0517   0.3059   0.9455
   6.500   0.6918   0.00992   0.00495   0.0518   0.3024   0.9462
   6.750   0.7176   0.01001   0.00502   0.0519   0.2985   0.9470
   7.000   0.7421   0.01009   0.00511   0.0523   0.2944   0.9480
   7.250   0.7669   0.01008   0.00514   0.0527   0.2910   0.9489
   7.500   0.7904   0.01010   0.00518   0.0533   0.2873   0.9500
   7.750   0.8130   0.01015   0.00522   0.0541   0.2833   0.9513
   8.000   0.8360   0.01021   0.00530   0.0547   0.2790   0.9524
   8.250   0.8615   0.01023   0.00536   0.0548   0.2747   0.9532
   8.500   0.8869   0.01030   0.00544   0.0549   0.2693   0.9539
   8.750   0.9120   0.01042   0.00556   0.0551   0.2643   0.9545
   9.000   0.9383   0.01049   0.00568   0.0551   0.2593   0.9551
   9.250   0.9633   0.01065   0.00583   0.0553   0.2524   0.9558
   9.500   0.9889   0.01076   0.00598   0.0553   0.2463   0.9564
   9.750   1.0137   0.01093   0.00615   0.0555   0.2393   0.9571
  10.000   1.0383   0.01110   0.00634   0.0556   0.2316   0.9578
  10.250   1.0618   0.01133   0.00656   0.0559   0.2229   0.9587
  10.500   1.0860   0.01153   0.00677   0.0561   0.2145   0.9596
  10.750   1.1088   0.01181   0.00705   0.0564   0.2042   0.9607
  11.000   1.1308   0.01217   0.00737   0.0567   0.1916   0.9618
  11.250   1.1526   0.01258   0.00774   0.0570   0.1781   0.9630
  11.500   1.1739   0.01304   0.00817   0.0573   0.1644   0.9640
  11.750   1.1914   0.01355   0.00863   0.0583   0.1498   0.9651
  12.000   1.2071   0.01414   0.00919   0.0596   0.1355   0.9665
  12.250   1.2208   0.01481   0.00981   0.0610   0.1215   0.9683
  12.500   1.2336   0.01548   0.01045   0.0625   0.1100   0.9703
  12.750   1.2434   0.01631   0.01124   0.0641   0.0968   0.9727
  13.000   1.2486   0.01718   0.01211   0.0665   0.0883   0.9751
  13.250   1.2559   0.01826   0.01319   0.0679   0.0796   0.9777
  13.500   1.2631   0.01962   0.01457   0.0684   0.0714   0.9808
  13.750   1.2703   0.02143   0.01638   0.0679   0.0634   0.9840
  14.000   1.2741   0.02365   0.01862   0.0672   0.0571   0.9883
  14.250   1.2816   0.02610   0.02112   0.0652   0.0513   0.9914
  14.500   1.2865   0.02886   0.02393   0.0633   0.0466   0.9947
  14.750   1.2890   0.03234   0.02745   0.0604   0.0419   0.9964
  15.000   1.2928   0.03559   0.03078   0.0577   0.0386   0.9975
  15.250   1.2892   0.03959   0.03484   0.0551   0.0355   0.9987
  15.500   1.2865   0.04328   0.03862   0.0529   0.0332   0.9999
  15.750   1.2710   0.04672   0.04212   0.0533   0.0317   1.0000
  16.000   1.2583   0.05074   0.04620   0.0523   0.0300   1.0000
  16.250   1.2472   0.05486   0.05039   0.0510   0.0284   1.0000
  16.500   1.2385   0.05887   0.05447   0.0495   0.0268   1.0000
  16.750   1.2282   0.06318   0.05884   0.0480   0.0253   1.0000
  17.000   1.2178   0.06755   0.06326   0.0464   0.0240   1.0000
  17.250   1.2114   0.07149   0.06728   0.0449   0.0227   1.0000
  17.500   1.2033   0.07569   0.07153   0.0433   0.0213   1.0000
  17.750   1.1932   0.08019   0.07609   0.0416   0.0201   1.0000
  18.000   1.1859   0.08441   0.08038   0.0400   0.0191   1.0000
  18.250   1.1796   0.08850   0.08453   0.0384   0.0180   1.0000
  18.500   1.1704   0.09302   0.08911   0.0366   0.0171   1.0000
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