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EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 340 AIRFOIL (e340-il)
Reynolds number: 500,000
Max Cl/Cd: 80.32 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e340-il-500000.txt
Download as CSV file: xf-e340-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5505   0.08509   0.08316  -0.0040   1.0000   0.0160
  -9.250  -0.5662   0.07853   0.07655  -0.0087   1.0000   0.0160
  -9.000  -0.5823   0.07344   0.07140  -0.0101   1.0000   0.0161
  -8.750  -0.5977   0.06905   0.06692  -0.0096   1.0000   0.0163
  -8.500  -0.6119   0.06465   0.06241  -0.0077   1.0000   0.0167
  -8.250  -0.6413   0.05528   0.05255  -0.0035   1.0000   0.0176
  -8.000  -0.6403   0.05327   0.05022  -0.0006   0.8420   0.0178
  -7.750  -0.6355   0.05152   0.04823   0.0016   0.7946   0.0180
  -7.500  -0.6280   0.04961   0.04610   0.0035   0.7626   0.0183
  -7.250  -0.6194   0.04730   0.04356   0.0054   0.7376   0.0188
  -7.000  -0.6099   0.04453   0.04053   0.0076   0.7168   0.0197
  -6.750  -0.6091   0.03895   0.03428   0.0124   0.7028   0.0217
  -6.500  -0.5930   0.03722   0.03244   0.0136   0.6846   0.0220
  -6.250  -0.5766   0.03555   0.03059   0.0150   0.6678   0.0226
  -6.000  -0.5593   0.03372   0.02852   0.0167   0.6524   0.0240
  -5.750  -0.5455   0.03091   0.02524   0.0195   0.6391   0.0265
  -5.500  -0.5246   0.02964   0.02386   0.0204   0.6243   0.0275
  -5.250  -0.5076   0.02792   0.02161   0.0230   0.6115   0.0313
  -5.000  -0.4740   0.01960   0.01219   0.0260   0.6026   0.0144
  -4.750  -0.4455   0.01851   0.01096   0.0261   0.5898   0.0139
  -4.500  -0.4163   0.01711   0.00943   0.0261   0.5774   0.0136
  -4.250  -0.3883   0.01607   0.00827   0.0264   0.5659   0.0134
  -4.000  -0.3618   0.01526   0.00734   0.0268   0.5548   0.0134
  -3.750  -0.3364   0.01459   0.00658   0.0275   0.5435   0.0135
  -3.500  -0.3118   0.01403   0.00594   0.0283   0.5333   0.0138
  -3.250  -0.2879   0.01352   0.00534   0.0292   0.5237   0.0143
  -3.000  -0.2643   0.01298   0.00480   0.0301   0.5145   0.0156
  -2.500  -0.2154   0.01227   0.00398   0.0317   0.4971   0.0217
  -2.250  -0.1929   0.01176   0.00359   0.0328   0.4891   0.0528
  -2.000  -0.1726   0.01107   0.00335   0.0341   0.4813   0.1546
  -1.750  -0.1710   0.00939   0.00292   0.0386   0.4754   0.4765
  -1.500  -0.1602   0.00854   0.00364   0.0432   0.4694   0.8495
  -1.250  -0.1500   0.00900   0.00404   0.0477   0.4631   0.8842
  -1.000  -0.0865   0.01101   0.00591   0.0427   0.4542   0.9028
  -0.750  -0.0586   0.01155   0.00638   0.0434   0.4474   0.9136
  -0.500   0.0167   0.01249   0.00712   0.0348   0.4381   0.9171
  -0.250   0.0481   0.01304   0.00761   0.0347   0.4320   0.9282
   0.000   0.1032   0.01330   0.00772   0.0296   0.4249   0.9309
   0.250   0.1399   0.01333   0.00768   0.0278   0.4191   0.9331
   0.500   0.1716   0.01332   0.00761   0.0269   0.4135   0.9354
   0.750   0.1966   0.01338   0.00759   0.0274   0.4089   0.9393
   1.000   0.2215   0.01341   0.00755   0.0278   0.4046   0.9426
   1.250   0.2563   0.01332   0.00744   0.0263   0.3999   0.9437
   1.500   0.2898   0.01329   0.00734   0.0250   0.3952   0.9450
   1.750   0.3219   0.01333   0.00729   0.0239   0.3905   0.9467
   2.000   0.3517   0.01329   0.00726   0.0234   0.3865   0.9488
   2.250   0.3754   0.01333   0.00728   0.0241   0.3824   0.9520
   2.500   0.4012   0.01334   0.00725   0.0243   0.3784   0.9544
   2.750   0.4342   0.01335   0.00718   0.0230   0.3742   0.9552
   3.000   0.4671   0.01329   0.00714   0.0218   0.3709   0.9564
   3.250   0.4983   0.01326   0.00711   0.0209   0.3672   0.9578
   3.500   0.5272   0.01326   0.00709   0.0205   0.3635   0.9593
   3.750   0.5540   0.01334   0.00712   0.0204   0.3597   0.9613
   4.000   0.5736   0.01348   0.00727   0.0219   0.3565   0.9640
   4.250   0.6057   0.01339   0.00721   0.0208   0.3528   0.9647
   4.500   0.6376   0.01334   0.00717   0.0197   0.3490   0.9655
   4.750   0.6690   0.01336   0.00718   0.0187   0.3455   0.9666
   5.000   0.6984   0.01348   0.00725   0.0180   0.3417   0.9678
   5.250   0.7261   0.01346   0.00730   0.0178   0.3385   0.9688
   5.500   0.7530   0.01349   0.00736   0.0177   0.3348   0.9702
   5.750   0.7769   0.01357   0.00746   0.0182   0.3312   0.9718
   6.000   0.7989   0.01373   0.00758   0.0191   0.3273   0.9730
   6.250   0.8288   0.01372   0.00764   0.0184   0.3237   0.9735
   6.500   0.8594   0.01370   0.00768   0.0175   0.3197   0.9743
   6.750   0.8894   0.01372   0.00772   0.0167   0.3155   0.9752
   7.000   0.9168   0.01388   0.00785   0.0164   0.3109   0.9759
   7.250   0.9432   0.01388   0.00795   0.0163   0.3069   0.9766
   7.500   0.9690   0.01392   0.00805   0.0164   0.3025   0.9772
   7.750   0.9943   0.01402   0.00817   0.0165   0.2982   0.9780
   8.000   1.0192   0.01417   0.00835   0.0167   0.2935   0.9791
   8.250   1.0426   0.01422   0.00848   0.0173   0.2883   0.9798
   8.500   1.0645   0.01434   0.00863   0.0181   0.2833   0.9803
   8.750   1.0850   0.01452   0.00885   0.0192   0.2784   0.9810
   9.000   1.1133   0.01454   0.00896   0.0186   0.2719   0.9815
   9.250   1.1408   0.01471   0.00912   0.0181   0.2651   0.9821
   9.500   1.1671   0.01477   0.00930   0.0180   0.2585   0.9827
   9.750   1.1902   0.01499   0.00951   0.0184   0.2510   0.9831
  10.000   1.2139   0.01513   0.00975   0.0187   0.2429   0.9836
  10.250   1.2355   0.01540   0.01003   0.0193   0.2349   0.9841
  10.500   1.2570   0.01565   0.01033   0.0199   0.2251   0.9846
  10.750   1.2779   0.01598   0.01069   0.0206   0.2139   0.9855
  11.000   1.2964   0.01640   0.01112   0.0216   0.2021   0.9865
  11.250   1.3110   0.01690   0.01162   0.0233   0.1898   0.9872
  11.500   1.3222   0.01748   0.01219   0.0256   0.1774   0.9882
  11.750   1.3398   0.01813   0.01282   0.0263   0.1630   0.9888
  12.000   1.3546   0.01888   0.01356   0.0274   0.1488   0.9897
  12.250   1.3660   0.01973   0.01441   0.0289   0.1357   0.9908
  12.500   1.3753   0.02071   0.01537   0.0306   0.1236   0.9927
  12.750   1.3755   0.02171   0.01638   0.0338   0.1142   0.9945
  13.000   1.3760   0.02271   0.01744   0.0363   0.1059   0.9962
  13.250   1.3739   0.02435   0.01912   0.0377   0.0984   0.9981
  13.500   1.3716   0.02663   0.02145   0.0378   0.0910   1.0000
  13.750   1.3530   0.02895   0.02384   0.0408   0.0876   1.0000
  14.000   1.3364   0.03138   0.02635   0.0434   0.0840   1.0000
  14.250   1.3158   0.03420   0.02923   0.0459   0.0809   1.0000
  14.500   1.2924   0.03726   0.03234   0.0485   0.0785   1.0000
  14.750   1.2711   0.04012   0.03527   0.0510   0.0762   1.0000
  15.000   1.2509   0.04307   0.03829   0.0530   0.0737   1.0000
  15.250   1.2327   0.04663   0.04191   0.0537   0.0708   1.0000
  15.500   1.2153   0.05087   0.04619   0.0531   0.0676   1.0000
  15.750   1.2057   0.05455   0.04995   0.0523   0.0642   1.0000
  16.000   1.1930   0.05886   0.05431   0.0510   0.0607   1.0000
  16.500   1.1722   0.06735   0.06290   0.0482   0.0543   1.0000
  16.750   1.1610   0.07185   0.06745   0.0466   0.0512   1.0000
  17.000   1.1495   0.07645   0.07209   0.0449   0.0486   1.0000
  17.250   1.1435   0.08042   0.07612   0.0434   0.0456   1.0000
  17.500   1.1329   0.08506   0.08080   0.0417   0.0430   1.0000
  17.750   1.1241   0.08949   0.08527   0.0400   0.0405   1.0000
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