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EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 426 AIRFOIL (e426-il)
Reynolds number: 50,000
Max Cl/Cd: 26.71 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e426-il-50000-n5.txt
Download as CSV file: xf-e426-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 426 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6398   0.11347   0.10562   0.0040   1.0000   0.0907
 -11.250  -0.6497   0.10707   0.09928   0.0005   1.0000   0.0936
 -11.000  -0.6760   0.09727   0.08957  -0.0058   1.0000   0.0959
 -10.750  -0.6618   0.09635   0.08864  -0.0048   1.0000   0.1000
 -10.500  -0.6690   0.09085   0.08318  -0.0076   1.0000   0.1036
 -10.250  -0.7075   0.07862   0.07104  -0.0165   1.0000   0.1059
 -10.000  -0.7647   0.06584   0.05828  -0.0263   1.0000   0.1053
  -9.750  -0.8058   0.05785   0.05008  -0.0296   1.0000   0.1062
  -9.500  -0.8244   0.05217   0.04403  -0.0307   1.0000   0.1098
  -9.250  -0.8035   0.05199   0.04388  -0.0296   1.0000   0.1158
  -9.000  -0.8149   0.04659   0.03780  -0.0302   1.0000   0.1218
  -8.750  -0.7896   0.04680   0.03819  -0.0291   1.0000   0.1277
  -8.500  -0.7849   0.04345   0.03428  -0.0289   1.0000   0.1350
  -8.250  -0.7635   0.04276   0.03365  -0.0281   1.0000   0.1410
  -8.000  -0.7492   0.04076   0.03126  -0.0276   1.0000   0.1486
  -7.750  -0.7305   0.03929   0.02967  -0.0270   1.0000   0.1547
  -7.500  -0.7108   0.03791   0.02811  -0.0264   1.0000   0.1610
  -7.250  -0.6940   0.03569   0.02535  -0.0260   1.0000   0.1670
  -7.000  -0.6713   0.03441   0.02407  -0.0254   1.0000   0.1709
  -6.750  -0.6494   0.03307   0.02257  -0.0248   1.0000   0.1760
  -6.500  -0.6281   0.03153   0.02063  -0.0243   1.0000   0.1819
  -6.250  -0.6049   0.03029   0.01934  -0.0237   1.0000   0.1862
  -6.000  -0.5814   0.02916   0.01811  -0.0231   1.0000   0.1908
  -5.750  -0.5581   0.02802   0.01674  -0.0225   1.0000   0.1969
  -5.500  -0.5345   0.02704   0.01571  -0.0218   1.0000   0.2029
  -5.250  -0.5109   0.02616   0.01478  -0.0211   1.0000   0.2098
  -5.000  -0.4868   0.02525   0.01370  -0.0205   1.0000   0.2169
  -4.750  -0.4632   0.02444   0.01296  -0.0197   1.0000   0.2233
  -4.500  -0.4393   0.02371   0.01208  -0.0190   1.0000   0.2323
  -4.250  -0.4162   0.02301   0.01152  -0.0181   1.0000   0.2412
  -4.000  -0.3928   0.02237   0.01086  -0.0173   1.0000   0.2517
  -3.750  -0.3697   0.02178   0.01030  -0.0165   1.0000   0.2635
  -3.500  -0.3469   0.02120   0.00983  -0.0156   1.0000   0.2762
  -3.250  -0.3239   0.02066   0.00939  -0.0149   1.0000   0.2915
  -3.000  -0.3019   0.02016   0.00901  -0.0140   1.0000   0.3095
  -2.750  -0.2804   0.01968   0.00867  -0.0130   1.0000   0.3304
  -2.500  -0.2598   0.01922   0.00845  -0.0119   1.0000   0.3557
  -2.250  -0.2400   0.01880   0.00827  -0.0108   1.0000   0.3886
  -2.000  -0.2212   0.01846   0.00819  -0.0094   1.0000   0.4313
  -1.750  -0.2038   0.01819   0.00821  -0.0078   1.0000   0.4829
  -1.500  -0.1824   0.01801   0.00834  -0.0069   0.9959   0.5403
  -1.250  -0.1416   0.01791   0.00852  -0.0093   0.9757   0.6083
  -1.000  -0.1011   0.01784   0.00867  -0.0112   0.9556   0.6699
  -0.750  -0.0619   0.01775   0.00876  -0.0126   0.9344   0.7237
  -0.500  -0.0156   0.01761   0.00877  -0.0147   0.9114   0.7768
  -0.250   0.0313   0.01743   0.00867  -0.0165   0.8807   0.8263
   0.000   0.0796   0.01728   0.00853  -0.0183   0.8454   0.8764
   0.250   0.1387   0.01718   0.00839  -0.0223   0.8091   0.9350
   0.500   0.2038   0.01705   0.00812  -0.0283   0.7695   0.9850
   0.750   0.2364   0.01704   0.00791  -0.0291   0.7338   1.0000
   1.000   0.2547   0.01713   0.00781  -0.0272   0.7015   1.0000
   1.250   0.2738   0.01726   0.00775  -0.0254   0.6689   1.0000
   1.500   0.2937   0.01743   0.00773  -0.0237   0.6354   1.0000
   1.750   0.3145   0.01764   0.00774  -0.0220   0.6011   1.0000
   2.000   0.3358   0.01788   0.00778  -0.0205   0.5653   1.0000
   2.250   0.3575   0.01816   0.00786  -0.0190   0.5286   1.0000
   2.500   0.3797   0.01850   0.00797  -0.0177   0.4923   1.0000
   2.750   0.4021   0.01889   0.00814  -0.0165   0.4573   1.0000
   3.000   0.4251   0.01933   0.00839  -0.0154   0.4251   1.0000
   3.250   0.4492   0.01982   0.00870  -0.0147   0.3970   1.0000
   3.500   0.4737   0.02036   0.00905  -0.0140   0.3748   1.0000
   3.750   0.4987   0.02091   0.00947  -0.0135   0.3553   1.0000
   4.000   0.5238   0.02148   0.00993  -0.0129   0.3381   1.0000
   4.250   0.5489   0.02207   0.01042  -0.0124   0.3236   1.0000
   4.500   0.5740   0.02269   0.01099  -0.0119   0.3099   1.0000
   4.750   0.5990   0.02332   0.01161  -0.0114   0.2969   1.0000
   5.000   0.6242   0.02401   0.01227  -0.0109   0.2858   1.0000
   5.250   0.6491   0.02471   0.01287  -0.0103   0.2756   1.0000
   5.500   0.6740   0.02546   0.01374  -0.0099   0.2651   1.0000
   5.750   0.6988   0.02626   0.01452  -0.0093   0.2561   1.0000
   6.000   0.7234   0.02708   0.01542  -0.0088   0.2469   1.0000
   6.250   0.7478   0.02800   0.01641  -0.0083   0.2387   1.0000
   6.500   0.7718   0.02890   0.01736  -0.0078   0.2301   1.0000
   6.750   0.7954   0.02993   0.01852  -0.0073   0.2222   1.0000
   7.000   0.8188   0.03096   0.01967  -0.0067   0.2144   1.0000
   7.250   0.8418   0.03206   0.02085  -0.0061   0.2073   1.0000
   7.500   0.8634   0.03326   0.02226  -0.0055   0.1993   1.0000
   7.750   0.8872   0.03428   0.02323  -0.0049   0.1935   1.0000
   8.000   0.9054   0.03589   0.02527  -0.0042   0.1856   1.0000
   8.250   0.9276   0.03691   0.02630  -0.0036   0.1794   1.0000
   8.500   0.9449   0.03868   0.02839  -0.0028   0.1730   1.0000
   8.750   0.9627   0.04017   0.03010  -0.0020   0.1664   1.0000
   9.000   0.9846   0.04119   0.03106  -0.0014   0.1614   1.0000
   9.250   0.9930   0.04383   0.03423  -0.0004   0.1550   1.0000
   9.500   1.0102   0.04516   0.03566   0.0004   0.1496   1.0000
   9.750   1.0238   0.04703   0.03771   0.0013   0.1450   1.0000
  10.000   1.0234   0.05037   0.04150   0.0022   0.1401   1.0000
  10.250   1.0347   0.05207   0.04333   0.0031   0.1356   1.0000
  10.500   1.0472   0.05375   0.04507   0.0039   0.1320   1.0000
  10.750   1.0203   0.05927   0.05104   0.0045   0.1294   1.0000
  11.000   0.9791   0.06568   0.05770   0.0041   0.1282   1.0000
  11.250   0.8814   0.08324   0.07534  -0.0078   0.1287   1.0000
  11.500   0.8244   0.09952   0.09155  -0.0189   0.1257   1.0000
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