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EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E854 AIRFOIL (e854-il)
Reynolds number: 50,000
Max Cl/Cd: 32.69 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e854-il-50000.txt
Download as CSV file: xf-e854-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E854 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3324   0.11197   0.10534  -0.0307   1.0000   0.2825
  -9.000  -0.3357   0.10953   0.10296  -0.0299   1.0000   0.2928
  -8.750  -0.3558   0.10901   0.10263  -0.0291   1.0000   0.3038
  -8.500  -0.3410   0.10491   0.09852  -0.0276   1.0000   0.3169
  -8.250  -0.3364   0.10122   0.09490  -0.0267   1.0000   0.3216
  -8.000  -0.3355   0.09815   0.09190  -0.0257   1.0000   0.3255
  -7.750  -0.3703   0.08183   0.07659  -0.0347   1.0000   0.1771
  -7.500  -0.4124   0.07481   0.06971  -0.0369   1.0000   0.1415
  -7.250  -0.5391   0.07333   0.06763  -0.0500   1.0000   0.1315
  -7.000  -0.5264   0.06976   0.06421  -0.0469   1.0000   0.1256
  -6.750  -0.5504   0.06336   0.05743  -0.0503   1.0000   0.1154
  -6.500  -0.5500   0.05922   0.05316  -0.0502   1.0000   0.1116
  -6.250  -0.5507   0.05296   0.04583  -0.0535   1.0000   0.1031
  -6.000  -0.5384   0.04909   0.04174  -0.0534   1.0000   0.1017
  -5.750  -0.5228   0.04537   0.03756  -0.0538   1.0000   0.1009
  -5.500  -0.5034   0.04228   0.03372  -0.0543   1.0000   0.1032
  -5.250  -0.4859   0.03962   0.03110  -0.0539   1.0000   0.1093
  -5.000  -0.4638   0.03711   0.02807  -0.0538   1.0000   0.1145
  -4.750  -0.4436   0.03508   0.02588  -0.0533   1.0000   0.1252
  -4.500  -0.4223   0.03318   0.02378  -0.0526   1.0000   0.1376
  -4.250  -0.4018   0.03170   0.02220  -0.0518   1.0000   0.1584
  -4.000  -0.3817   0.03016   0.02075  -0.0508   1.0000   0.1878
  -3.750  -0.3615   0.02848   0.01954  -0.0502   1.0000   0.2371
  -3.500  -0.3428   0.02707   0.01984  -0.0486   1.0000   0.4286
  -3.250  -0.3397   0.02870   0.02179  -0.0419   1.0000   0.5533
  -3.000  -0.3358   0.02982   0.02291  -0.0360   1.0000   0.6070
  -2.750  -0.3322   0.03058   0.02365  -0.0304   1.0000   0.6453
  -2.500  -0.3212   0.03131   0.02427  -0.0263   0.9969   0.6842
  -2.250  -0.3018   0.03212   0.02491  -0.0234   0.9881   0.7231
  -2.000  -0.2845   0.03265   0.02531  -0.0204   0.9797   0.7581
  -1.750  -0.2671   0.03302   0.02554  -0.0176   0.9716   0.7923
  -1.500  -0.2532   0.03301   0.02540  -0.0149   0.9636   0.8219
  -1.250  -0.2332   0.03307   0.02530  -0.0136   0.9561   0.8495
  -1.000  -0.2095   0.03307   0.02510  -0.0137   0.9483   0.8734
  -0.750  -0.1840   0.03310   0.02496  -0.0145   0.9409   0.8954
  -0.500  -0.1448   0.03342   0.02509  -0.0180   0.9333   0.9186
  -0.250  -0.1034   0.03373   0.02522  -0.0225   0.9255   0.9423
   0.000  -0.0294   0.03466   0.02590  -0.0332   0.9174   0.9675
   0.250   0.0270   0.03524   0.02630  -0.0416   0.9091   1.0000
   0.500   0.0443   0.03546   0.02636  -0.0434   0.9023   1.0000
   0.750   0.0678   0.03591   0.02665  -0.0461   0.8953   1.0000
   1.000   0.1078   0.03677   0.02733  -0.0513   0.8885   1.0000
   1.250   0.1360   0.03756   0.02795  -0.0545   0.8818   1.0000
   1.500   0.1798   0.03868   0.02888  -0.0599   0.8752   1.0000
   1.750   0.2013   0.03960   0.02967  -0.0616   0.8688   1.0000
   2.000   0.2411   0.04080   0.03071  -0.0657   0.8625   1.0000
   2.250   0.2590   0.04186   0.03167  -0.0665   0.8565   1.0000
   2.500   0.2874   0.04305   0.03276  -0.0686   0.8504   1.0000
   2.750   0.3126   0.04431   0.03393  -0.0701   0.8446   1.0000
   3.000   0.3301   0.04554   0.03509  -0.0705   0.8390   1.0000
   3.250   0.3654   0.04693   0.03643  -0.0732   0.8324   1.0000
   3.500   0.3733   0.04821   0.03768  -0.0723   0.8274   1.0000
   3.750   0.3985   0.04962   0.03906  -0.0736   0.8212   1.0000
   4.000   0.4167   0.05107   0.04051  -0.0739   0.8150   1.0000
   4.250   0.4325   0.05254   0.04199  -0.0741   0.8094   1.0000
   4.500   0.4583   0.05408   0.04353  -0.0753   0.8016   1.0000
   4.750   0.4696   0.05564   0.04512  -0.0750   0.7960   1.0000
   5.000   0.4957   0.05723   0.04675  -0.0762   0.7870   1.0000
   5.250   0.5112   0.05884   0.04843  -0.0763   0.7793   1.0000
   5.500   0.5292   0.06050   0.05015  -0.0766   0.7702   1.0000
   5.750   0.5559   0.06208   0.05180  -0.0776   0.7581   1.0000
   6.000   0.5838   0.06363   0.05347  -0.0787   0.7452   1.0000
   6.250   0.6105   0.06513   0.05508  -0.0795   0.7314   1.0000
   6.500   0.6338   0.06663   0.05669  -0.0798   0.7171   1.0000
   6.750   0.6533   0.06815   0.05832  -0.0798   0.7020   1.0000
   7.000   0.6701   0.06970   0.06002  -0.0794   0.6860   1.0000
   7.250   0.6879   0.07123   0.06168  -0.0791   0.6689   1.0000
   7.500   0.7158   0.07234   0.06297  -0.0792   0.6496   1.0000
   7.750   0.7523   0.07298   0.06381  -0.0794   0.6291   1.0000
   8.000   0.7662   0.07443   0.06544  -0.0785   0.6092   1.0000
   8.250   0.8178   0.07366   0.06498  -0.0785   0.5868   1.0000
   8.500   0.8277   0.07504   0.06652  -0.0770   0.5645   1.0000
   8.750   0.8689   0.07398   0.06575  -0.0757   0.5406   1.0000
   9.000   0.9407   0.06903   0.06133  -0.0736   0.5145   1.0000
   9.250   1.1800   0.04063   0.03438  -0.0688   0.4548   1.0000
   9.500   1.2005   0.03672   0.03026  -0.0622   0.3845   1.0000
   9.750   1.1942   0.03722   0.03008  -0.0561   0.3189   1.0000
  10.000   1.1873   0.03945   0.03164  -0.0517   0.2677   1.0000
  10.250   1.1872   0.04211   0.03379  -0.0485   0.2261   1.0000
  10.500   1.2018   0.04485   0.03612  -0.0466   0.1877   1.0000
  10.750   1.2227   0.04778   0.03888  -0.0455   0.1574   1.0000
  11.000   1.2528   0.05108   0.04201  -0.0455   0.1321   1.0000
  11.250   1.2747   0.05470   0.04581  -0.0448   0.1166   1.0000
  11.500   1.2934   0.05865   0.04992  -0.0441   0.1053   1.0000
  11.750   1.3176   0.06319   0.05447  -0.0443   0.0948   1.0000
  12.000   1.3014   0.06619   0.05796  -0.0404   0.0930   1.0000
  12.250   1.2867   0.06979   0.06197  -0.0374   0.0912   1.0000
  12.500   1.2716   0.07383   0.06637  -0.0351   0.0900   1.0000
  12.750   1.2536   0.07820   0.07107  -0.0334   0.0896   1.0000
  13.000   1.2320   0.08295   0.07613  -0.0325   0.0896   1.0000
  13.250   1.2075   0.08821   0.08166  -0.0324   0.0902   1.0000
  13.500   1.1813   0.09408   0.08778  -0.0333   0.0910   1.0000
  13.750   1.1548   0.10054   0.09443  -0.0351   0.0920   1.0000
  14.000   1.1288   0.10758   0.10163  -0.0378   0.0931   1.0000
  14.250   1.1056   0.11505   0.10922  -0.0411   0.0941   1.0000
  14.500   1.0860   0.12287   0.11711  -0.0446   0.0949   1.0000
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