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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.06 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e178-il-1000000.txt
Download as CSV file: xf-e178-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E178  (8.69%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4078   0.12422   0.12280   0.0065   1.0000   0.0079
 -11.000  -0.4042   0.12006   0.11864   0.0047   1.0000   0.0087
 -10.750  -0.4841   0.12054   0.11895   0.0038   1.0000   0.0076
 -10.500  -0.4794   0.11670   0.11512   0.0021   1.0000   0.0076
 -10.250  -0.4746   0.11285   0.11128   0.0003   1.0000   0.0083
  -6.500  -0.4441   0.03178   0.02897  -0.0455   0.8054   0.0084
  -6.250  -0.4421   0.01951   0.01544  -0.0443   0.7936   0.0079
  -6.000  -0.4184   0.01772   0.01331  -0.0438   0.7812   0.0087
  -5.750  -0.3927   0.01681   0.01216  -0.0434   0.7696   0.0092
  -5.250  -0.3444   0.01321   0.00794  -0.0425   0.7492   0.0106
  -5.000  -0.3178   0.01270   0.00735  -0.0423   0.7396   0.0113
  -4.750  -0.2907   0.01239   0.00695  -0.0422   0.7309   0.0123
  -4.500  -0.2634   0.01206   0.00653  -0.0421   0.7223   0.0135
  -4.250  -0.2361   0.01161   0.00597  -0.0419   0.7145   0.0142
  -4.000  -0.2087   0.01127   0.00553  -0.0417   0.7069   0.0147
  -3.750  -0.1825   0.01031   0.00443  -0.0414   0.7000   0.0153
  -3.500  -0.1567   0.00935   0.00332  -0.0410   0.6932   0.0172
  -3.250  -0.1293   0.00899   0.00289  -0.0408   0.6867   0.0185
  -3.000  -0.1017   0.00870   0.00252  -0.0407   0.6803   0.0195
  -2.750  -0.0739   0.00845   0.00220  -0.0406   0.6743   0.0203
  -2.500  -0.0461   0.00823   0.00191  -0.0405   0.6682   0.0212
  -2.250  -0.0182   0.00808   0.00168  -0.0404   0.6626   0.0224
  -2.000   0.0099   0.00784   0.00142  -0.0403   0.6568   0.0287
  -1.750   0.0371   0.00750   0.00125  -0.0403   0.6513   0.0815
  -1.500   0.0646   0.00721   0.00114  -0.0403   0.6461   0.1406
  -1.250   0.0919   0.00689   0.00106  -0.0403   0.6405   0.2195
  -1.000   0.1190   0.00663   0.00100  -0.0403   0.6353   0.2986
  -0.750   0.1461   0.00627   0.00096  -0.0403   0.6301   0.4022
  -0.500   0.1723   0.00586   0.00093  -0.0401   0.6248   0.5382
  -0.250   0.1974   0.00542   0.00093  -0.0397   0.6198   0.6881
   0.000   0.2184   0.00487   0.00096  -0.0379   0.6146   0.8688
   0.250   0.2644   0.00474   0.00098  -0.0415   0.6091   0.9847
   0.500   0.3104   0.00475   0.00095  -0.0455   0.6035   0.9993
   0.750   0.3388   0.00479   0.00094  -0.0456   0.5976   1.0000
   1.000   0.3654   0.00484   0.00094  -0.0453   0.5911   1.0000
   1.250   0.3920   0.00488   0.00094  -0.0450   0.5838   1.0000
   1.500   0.4188   0.00493   0.00096  -0.0447   0.5773   1.0000
   1.750   0.4455   0.00498   0.00098  -0.0445   0.5700   1.0000
   2.000   0.4724   0.00503   0.00100  -0.0442   0.5626   1.0000
   2.250   0.4992   0.00510   0.00103  -0.0440   0.5547   1.0000
   2.500   0.5262   0.00515   0.00108  -0.0438   0.5467   1.0000
   2.750   0.5531   0.00523   0.00113  -0.0436   0.5380   1.0000
   3.000   0.5803   0.00530   0.00118  -0.0434   0.5289   1.0000
   3.250   0.6074   0.00537   0.00124  -0.0432   0.5201   1.0000
   3.500   0.6344   0.00547   0.00132  -0.0431   0.5096   1.0000
   3.750   0.6615   0.00558   0.00140  -0.0429   0.4975   1.0000
   4.000   0.6885   0.00569   0.00149  -0.0428   0.4839   1.0000
   4.250   0.7156   0.00581   0.00159  -0.0427   0.4684   1.0000
   4.500   0.7426   0.00595   0.00171  -0.0425   0.4522   1.0000
   4.750   0.7691   0.00615   0.00185  -0.0424   0.4279   1.0000
   5.000   0.7953   0.00642   0.00201  -0.0422   0.3954   1.0000
   5.250   0.8193   0.00702   0.00231  -0.0418   0.3241   1.0000
   5.500   0.8419   0.00785   0.00276  -0.0413   0.2413   1.0000
   5.750   0.8645   0.00865   0.00321  -0.0409   0.1708   1.0000
   6.000   0.8882   0.00928   0.00361  -0.0405   0.1250   1.0000
   6.250   0.9119   0.00986   0.00402  -0.0401   0.0895   1.0000
   6.500   0.9360   0.01039   0.00442  -0.0397   0.0628   1.0000
   6.750   0.9591   0.01102   0.00490  -0.0393   0.0354   1.0000
   7.000   0.9797   0.01205   0.00577  -0.0383   0.0085   1.0000
   7.250   1.0039   0.01250   0.00628  -0.0379   0.0074   1.0000
   7.500   1.0274   0.01303   0.00684  -0.0373   0.0064   1.0000
   7.750   1.0497   0.01371   0.00760  -0.0366   0.0058   1.0000
   8.000   1.0686   0.01479   0.00883  -0.0354   0.0053   1.0000
   8.250   1.0908   0.01538   0.00949  -0.0347   0.0052   1.0000
   8.500   1.1121   0.01604   0.01023  -0.0339   0.0050   1.0000
   8.750   1.1317   0.01685   0.01113  -0.0329   0.0049   1.0000
   9.000   1.1512   0.01763   0.01199  -0.0319   0.0046   1.0000
   9.250   1.1687   0.01858   0.01302  -0.0306   0.0044   1.0000
   9.500   1.1859   0.01949   0.01401  -0.0294   0.0041   1.0000
   9.750   1.2012   0.02052   0.01512  -0.0279   0.0038   1.0000
  10.000   1.2137   0.02176   0.01648  -0.0261   0.0038   1.0000
  10.250   1.2250   0.02302   0.01783  -0.0243   0.0036   1.0000
  10.500   1.2312   0.02442   0.01935  -0.0216   0.0036   1.0000
  10.750   1.2352   0.02587   0.02091  -0.0189   0.0036   1.0000
  11.000   1.2384   0.02760   0.02280  -0.0164   0.0036   1.0000
  11.250   1.2403   0.02965   0.02502  -0.0142   0.0036   1.0000
  11.500   1.2409   0.03206   0.02762  -0.0122   0.0036   1.0000
  11.750   1.2313   0.03640   0.03234  -0.0097   0.0039   1.0000
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