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EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 431 AIRFOIL (e431-il)
Reynolds number: 50,000
Max Cl/Cd: 19.81 at α=12°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e431-il-50000-n5.txt
Download as CSV file: xf-e431-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 431 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2867   0.10946   0.10306  -0.0672   0.9685   0.0467
  -9.250  -0.2774   0.10569   0.09929  -0.0693   0.9629   0.0454
  -9.000  -0.2706   0.10115   0.09476  -0.0730   0.9579   0.0440
  -8.750  -0.2720   0.09672   0.09037  -0.0759   0.9504   0.0427
  -8.500  -0.2915   0.08799   0.08161  -0.0849   0.9419   0.0397
  -8.250  -0.2938   0.08451   0.07812  -0.0865   0.9345   0.0393
  -8.000  -0.3007   0.08103   0.07461  -0.0881   0.9272   0.0389
  -7.750  -0.3093   0.07766   0.07120  -0.0889   0.9189   0.0385
  -7.500  -0.3165   0.07393   0.06735  -0.0897   0.9114   0.0381
  -7.250  -0.3225   0.07058   0.06387  -0.0897   0.9036   0.0376
  -7.000  -0.3224   0.06651   0.05955  -0.0907   0.8979   0.0373
  -6.750  -0.3289   0.06388   0.05674  -0.0887   0.8897   0.0369
  -6.500  -0.3205   0.05993   0.05241  -0.0896   0.8849   0.0366
  -6.250  -0.3199   0.05711   0.04928  -0.0879   0.8782   0.0368
  -6.000  -0.3106   0.05414   0.04591  -0.0872   0.8725   0.0373
  -5.750  -0.2906   0.05087   0.04209  -0.0880   0.8688   0.0382
  -5.500  -0.2798   0.04847   0.03915  -0.0864   0.8630   0.0392
  -5.250  -0.2632   0.04641   0.03677  -0.0856   0.8578   0.0406
  -5.000  -0.2377   0.04446   0.03455  -0.0861   0.8542   0.0422
  -4.750  -0.2064   0.04227   0.03192  -0.0869   0.8516   0.0439
  -4.500  -0.1953   0.04124   0.03060  -0.0844   0.8452   0.0454
  -4.250  -0.1712   0.03994   0.02905  -0.0838   0.8408   0.0493
  -4.000  -0.1419   0.03880   0.02772  -0.0839   0.8377   0.0543
  -3.750  -0.1096   0.03766   0.02647  -0.0843   0.8352   0.0608
  -3.500  -0.1018   0.03741   0.02606  -0.0809   0.8282   0.0674
  -3.250  -0.0785   0.03668   0.02529  -0.0801   0.8240   0.0797
  -3.000  -0.0510   0.03573   0.02440  -0.0803   0.8208   0.1023
  -2.750  -0.0339   0.03503   0.02384  -0.0791   0.8159   0.1378
  -2.500  -0.0198   0.03385   0.02335  -0.0781   0.8102   0.2293
  -2.250  -0.0201   0.03250   0.02424  -0.0713   0.8062   0.6023
  -2.000  -0.0051   0.03324   0.02481  -0.0664   0.8028   0.7656
  -1.750  -0.0117   0.03402   0.02552  -0.0596   0.7945   0.8064
  -1.500  -0.0037   0.03444   0.02578  -0.0537   0.7899   0.8542
  -1.250   0.0233   0.03480   0.02594  -0.0501   0.7873   0.9166
  -1.000   0.1610   0.03557   0.02599  -0.0691   0.7883   0.9667
  -0.750   0.1922   0.03587   0.02606  -0.0711   0.7827   0.9751
  -0.500   0.2220   0.03617   0.02614  -0.0729   0.7770   0.9826
  -0.250   0.2615   0.03624   0.02599  -0.0759   0.7733   0.9879
   0.000   0.3033   0.03622   0.02574  -0.0791   0.7706   0.9927
   0.250   0.3034   0.03700   0.02647  -0.0763   0.7609   1.0000
   0.500   0.3225   0.03707   0.02640  -0.0755   0.7564   1.0000
   1.000   0.3227   0.03778   0.02698  -0.0681   0.7417   1.0000
   1.500   0.3263   0.03846   0.02751  -0.0613   0.7272   1.0000
   1.750   0.3520   0.03851   0.02744  -0.0613   0.7233   1.0000
   2.000   0.3469   0.03928   0.02817  -0.0576   0.7134   1.0000
   2.250   0.3741   0.03949   0.02828  -0.0580   0.7088   1.0000
   2.500   0.3853   0.04021   0.02893  -0.0567   0.7008   1.0000
   2.750   0.4083   0.04066   0.02932  -0.0568   0.6947   1.0000
   3.000   0.4429   0.04079   0.02937  -0.0582   0.6911   1.0000
   3.250   0.4489   0.04190   0.03045  -0.0566   0.6806   1.0000
   3.500   0.4820   0.04209   0.03059  -0.0578   0.6764   1.0000
   3.750   0.4928   0.04314   0.03164  -0.0568   0.6666   1.0000
   4.000   0.5237   0.04342   0.03190  -0.0577   0.6615   1.0000
   4.250   0.5383   0.04440   0.03287  -0.0572   0.6526   1.0000
   4.500   0.5668   0.04476   0.03322  -0.0578   0.6465   1.0000
   5.000   0.6107   0.04607   0.03455  -0.0579   0.6312   1.0000
   5.500   0.6551   0.04733   0.03588  -0.0579   0.6156   1.0000
   6.000   0.7001   0.04849   0.03713  -0.0579   0.5996   1.0000
   6.250   0.7126   0.04968   0.03840  -0.0572   0.5889   1.0000
   6.500   0.7453   0.04956   0.03835  -0.0577   0.5835   1.0000
   6.750   0.7556   0.05090   0.03975  -0.0568   0.5718   1.0000
   7.000   0.7912   0.05047   0.03943  -0.0574   0.5671   1.0000
   7.250   0.7998   0.05193   0.04097  -0.0564   0.5546   1.0000
   7.500   0.8379   0.05114   0.04029  -0.0570   0.5506   1.0000
   7.750   0.8455   0.05269   0.04193  -0.0559   0.5375   1.0000
   8.000   0.8566   0.05400   0.04335  -0.0551   0.5255   1.0000
   8.250   0.8929   0.05309   0.04258  -0.0552   0.5206   1.0000
   8.500   0.9018   0.05456   0.04415  -0.0543   0.5076   1.0000
   9.000   0.9501   0.05454   0.04443  -0.0533   0.4902   1.0000
   9.250   0.9601   0.05590   0.04590  -0.0524   0.4771   1.0000
   9.750   1.0121   0.05526   0.04559  -0.0512   0.4590   1.0000
  10.000   1.0228   0.05651   0.04698  -0.0503   0.4457   1.0000
  10.500   1.0747   0.05568   0.04647  -0.0488   0.4251   1.0000
  10.750   1.0941   0.05592   0.04686  -0.0480   0.4125   1.0000
  11.000   1.1077   0.05681   0.04791  -0.0470   0.3984   1.0000
  11.250   1.1233   0.05749   0.04873  -0.0461   0.3845   1.0000
  11.500   1.1402   0.05801   0.04937  -0.0452   0.3703   1.0000
  11.750   1.1572   0.05852   0.04999  -0.0443   0.3557   1.0000
  12.000   1.1726   0.05920   0.05079  -0.0433   0.3404   1.0000
  12.250   1.1859   0.06014   0.05183  -0.0424   0.3249   1.0000
  12.500   1.1971   0.06133   0.05309  -0.0414   0.3091   1.0000
  12.750   1.2062   0.06280   0.05462  -0.0406   0.2933   1.0000
  13.000   1.2136   0.06450   0.05639  -0.0398   0.2779   1.0000
  13.250   1.2192   0.06646   0.05843  -0.0390   0.2628   1.0000
  13.500   1.2233   0.06864   0.06068  -0.0384   0.2479   1.0000
  13.750   1.2263   0.07103   0.06313  -0.0379   0.2338   1.0000
  14.000   1.2284   0.07359   0.06574  -0.0375   0.2200   1.0000
  14.250   1.2303   0.07623   0.06843  -0.0372   0.2068   1.0000
  14.500   1.2322   0.07890   0.07113  -0.0370   0.1943   1.0000
  14.750   1.2348   0.08149   0.07374  -0.0368   0.1821   1.0000
  15.000   1.2297   0.08545   0.07788  -0.0372   0.1710   1.0000
  15.250   1.2271   0.08910   0.08165  -0.0377   0.1604   1.0000
  15.500   1.2271   0.09232   0.08490  -0.0380   0.1504   1.0000
  15.750   1.2273   0.09553   0.08814  -0.0385   0.1408   1.0000
  16.000   1.2204   0.10020   0.09302  -0.0397   0.1324   1.0000
  16.250   1.2215   0.10340   0.09622  -0.0403   0.1242   1.0000
  16.500   1.2155   0.10806   0.10106  -0.0418   0.1168   1.0000
  16.750   1.2136   0.11197   0.10504  -0.0430   0.1100   1.0000
  17.000   1.2080   0.11669   0.10992  -0.0447   0.1037   1.0000
  17.250   1.2063   0.12070   0.11402  -0.0462   0.0979   1.0000
  17.500   1.1948   0.12691   0.12047  -0.0490   0.0934   1.0000
  17.750   1.2020   0.12907   0.12255  -0.0497   0.0874   1.0000
  18.000   1.1814   0.13761   0.13141  -0.0542   0.0848   1.0000
  18.250   1.1597   0.14678   0.14082  -0.0593   0.0824   1.0000
  18.500   1.1808   0.14561   0.13951  -0.0582   0.0763   1.0000
  18.750   1.1493   0.15766   0.15182  -0.0655   0.0754   1.0000
  19.000   1.1031   0.17526   0.16947  -0.0761   0.0752   1.0000
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