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EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 520 AIRFOIL (e520-il)
Reynolds number: 50,000
Max Cl/Cd: 28.39 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e520-il-50000.txt
Download as CSV file: xf-e520-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 520 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6157   0.13574   0.12877   0.0019   1.0000   0.2023
 -12.750  -0.5919   0.13254   0.12549   0.0032   1.0000   0.2132
 -12.500  -0.7961   0.08828   0.08171  -0.0309   1.0000   0.1312
 -12.250  -0.8203   0.08142   0.07479  -0.0334   1.0000   0.1303
 -12.000  -0.8489   0.07522   0.06850  -0.0352   1.0000   0.1293
 -11.750  -0.8764   0.06992   0.06306  -0.0358   1.0000   0.1285
 -11.500  -0.9033   0.06538   0.05834  -0.0352   1.0000   0.1280
 -11.250  -0.9275   0.06153   0.05427  -0.0331   1.0000   0.1282
 -11.000  -0.9469   0.05782   0.05023  -0.0307   1.0000   0.1291
 -10.750  -0.9624   0.05423   0.04619  -0.0281   1.0000   0.1307
 -10.500  -0.9445   0.05151   0.04358  -0.0276   1.0000   0.1406
 -10.250  -0.9546   0.04837   0.03988  -0.0247   1.0000   0.1451
 -10.000  -0.9352   0.04558   0.03716  -0.0241   1.0000   0.1563
  -9.750  -0.9232   0.04323   0.03475  -0.0228   1.0000   0.1692
  -9.500  -0.9103   0.04086   0.03229  -0.0214   1.0000   0.1834
  -9.250  -0.8999   0.03881   0.03015  -0.0196   1.0000   0.2005
  -9.000  -0.8843   0.03688   0.02832  -0.0182   1.0000   0.2208
  -8.750  -0.8734   0.03533   0.02680  -0.0161   1.0000   0.2435
  -8.500  -0.8617   0.03393   0.02560  -0.0138   1.0000   0.2681
  -8.250  -0.8627   0.03274   0.02436  -0.0098   1.0000   0.2905
  -8.000  -0.8554   0.03178   0.02366  -0.0065   1.0000   0.3172
  -7.750  -0.8512   0.03095   0.02302  -0.0027   1.0000   0.3454
  -7.500  -0.8467   0.03018   0.02240   0.0011   1.0000   0.3762
  -7.250  -0.8410   0.02958   0.02197   0.0049   1.0000   0.4099
  -7.000  -0.8268   0.02958   0.02224   0.0084   1.0000   0.4473
  -6.750  -0.8150   0.02976   0.02252   0.0122   1.0000   0.4840
  -6.500  -0.7864   0.03156   0.02447   0.0155   1.0000   0.5196
  -6.250  -0.7563   0.03376   0.02663   0.0189   1.0000   0.5498
  -6.000  -0.7251   0.03610   0.02885   0.0222   1.0000   0.5758
  -5.750  -0.7125   0.03700   0.02960   0.0263   1.0000   0.6006
  -5.500  -0.6612   0.04034   0.03272   0.0281   1.0000   0.6211
  -5.250  -0.6598   0.04029   0.03258   0.0325   1.0000   0.6443
  -5.000  -0.6101   0.04254   0.03460   0.0332   1.0000   0.6640
  -4.750  -0.6034   0.04247   0.03439   0.0368   1.0000   0.6861
  -4.500  -0.5682   0.04326   0.03500   0.0376   1.0000   0.7064
  -4.250  -0.5390   0.04355   0.03513   0.0384   1.0000   0.7274
  -4.000  -0.5320   0.04310   0.03458   0.0415   1.0000   0.7486
  -3.750  -0.4742   0.04347   0.03470   0.0378   1.0000   0.7690
  -3.500  -0.4628   0.04296   0.03408   0.0398   1.0000   0.7897
  -3.250  -0.4212   0.04270   0.03366   0.0373   1.0000   0.8093
  -3.000  -0.3822   0.04233   0.03313   0.0349   1.0000   0.8285
  -2.750  -0.3600   0.04180   0.03250   0.0347   1.0000   0.8472
  -2.500  -0.3457   0.04125   0.03187   0.0355   1.0000   0.8653
  -2.250  -0.3045   0.04077   0.03126   0.0319   1.0000   0.8821
  -2.000  -0.2698   0.04029   0.03069   0.0291   1.0000   0.8984
  -1.750  -0.2372   0.03982   0.03014   0.0264   1.0000   0.9141
  -1.500  -0.2052   0.03939   0.02962   0.0235   1.0000   0.9290
  -1.250  -0.1721   0.03900   0.02918   0.0202   1.0000   0.9433
  -1.000  -0.1391   0.03867   0.02879   0.0168   1.0000   0.9568
  -0.750  -0.1049   0.03842   0.02850   0.0130   1.0000   0.9696
  -0.500  -0.0672   0.03825   0.02830   0.0083   1.0000   0.9820
  -0.250  -0.0247   0.03811   0.02814   0.0026   1.0000   0.9938
   0.000   0.0000   0.03808   0.02810   0.0000   1.0000   1.0000
   0.250   0.0245   0.03810   0.02813  -0.0025   0.9938   1.0000
   0.500   0.0671   0.03824   0.02829  -0.0083   0.9820   1.0000
   0.750   0.1046   0.03841   0.02849  -0.0129   0.9697   1.0000
   1.000   0.1385   0.03866   0.02878  -0.0167   0.9569   1.0000
   1.250   0.1718   0.03899   0.02916  -0.0202   0.9434   1.0000
   1.500   0.2040   0.03937   0.02961  -0.0233   0.9294   1.0000
   1.750   0.2361   0.03981   0.03012  -0.0262   0.9144   1.0000
   2.000   0.2676   0.04028   0.03067  -0.0287   0.8989   1.0000
   2.250   0.3025   0.04076   0.03125  -0.0316   0.8824   1.0000
   2.500   0.3439   0.04123   0.03185  -0.0352   0.8655   1.0000
   2.750   0.3604   0.04177   0.03247  -0.0347   0.8473   1.0000
   3.000   0.3828   0.04229   0.03309  -0.0350   0.8284   1.0000
   3.250   0.4219   0.04265   0.03362  -0.0374   0.8093   1.0000
   3.500   0.4643   0.04290   0.03403  -0.0400   0.7898   1.0000
   3.750   0.4740   0.04345   0.03468  -0.0378   0.7693   1.0000
   4.000   0.5298   0.04313   0.03460  -0.0412   0.7488   1.0000
   4.250   0.5398   0.04351   0.03509  -0.0385   0.7278   1.0000
   4.500   0.5674   0.04326   0.03500  -0.0375   0.7066   1.0000
   4.750   0.6049   0.04239   0.03432  -0.0370   0.6863   1.0000
   5.000   0.6102   0.04251   0.03456  -0.0332   0.6641   1.0000
   5.250   0.6593   0.04028   0.03256  -0.0324   0.6444   1.0000
   5.500   0.6615   0.04027   0.03266  -0.0281   0.6210   1.0000
   5.750   0.7121   0.03700   0.02960  -0.0262   0.6006   1.0000
   6.000   0.7249   0.03607   0.02882  -0.0222   0.5758   1.0000
   6.250   0.7560   0.03375   0.02662  -0.0189   0.5499   1.0000
   6.500   0.7861   0.03153   0.02443  -0.0155   0.5195   1.0000
   6.750   0.8143   0.02977   0.02253  -0.0121   0.4842   1.0000
   7.000   0.8264   0.02956   0.02222  -0.0083   0.4476   1.0000
   7.250   0.8401   0.02959   0.02199  -0.0048   0.4103   1.0000
   7.500   0.8464   0.03016   0.02239  -0.0011   0.3763   1.0000
   7.750   0.8510   0.03093   0.02300   0.0027   0.3457   1.0000
   8.000   0.8553   0.03177   0.02364   0.0065   0.3175   1.0000
   8.250   0.8609   0.03274   0.02442   0.0100   0.2914   1.0000
   8.500   0.8617   0.03393   0.02559   0.0138   0.2683   1.0000
   8.750   0.8737   0.03534   0.02680   0.0160   0.2435   1.0000
   9.000   0.8847   0.03689   0.02833   0.0181   0.2207   1.0000
   9.250   0.9003   0.03885   0.03018   0.0195   0.2004   1.0000
   9.500   0.9108   0.04089   0.03232   0.0213   0.1834   1.0000
   9.750   0.9236   0.04325   0.03478   0.0227   0.1691   1.0000
  10.000   0.9359   0.04563   0.03721   0.0240   0.1563   1.0000
  10.250   0.9550   0.04840   0.03991   0.0246   0.1450   1.0000
  10.500   0.9445   0.05152   0.04359   0.0275   0.1401   1.0000
  10.750   0.9626   0.05425   0.04622   0.0280   0.1306   1.0000
  11.000   0.9469   0.05788   0.05030   0.0306   0.1290   1.0000
  11.250   0.9278   0.06160   0.05434   0.0330   0.1281   1.0000
  11.500   0.9031   0.06547   0.05844   0.0350   0.1279   1.0000
  11.750   0.8765   0.07003   0.06318   0.0356   0.1284   1.0000
  12.000   0.8482   0.07539   0.06868   0.0350   0.1292   1.0000
  12.250   0.8206   0.08158   0.07496   0.0332   0.1303   1.0000
  12.500   0.7950   0.08859   0.08202   0.0305   0.1312   1.0000
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