Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E474 (14.09%) (e474-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E474 (14.09%) (e474-il)
Reynolds number: 200,000
Max Cl/Cd: 45.33 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e474-il-200000.txt
Download as CSV file: xf-e474-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E474  (14.09%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.9940   0.12317   0.11888  -0.0091   1.0000   0.0580
 -18.250  -1.0516   0.10822   0.10365  -0.0182   1.0000   0.0583
 -18.000  -1.0877   0.09793   0.09312  -0.0245   1.0000   0.0591
 -17.750  -1.0758   0.09691   0.09226  -0.0242   1.0000   0.0621
 -17.500  -1.0883   0.09126   0.08656  -0.0274   1.0000   0.0642
 -17.250  -1.1128   0.08369   0.07883  -0.0319   1.0000   0.0658
 -17.000  -1.1386   0.07617   0.07112  -0.0363   1.0000   0.0672
 -16.750  -1.1631   0.06910   0.06382  -0.0405   1.0000   0.0684
 -16.500  -1.1639   0.06623   0.06108  -0.0413   1.0000   0.0714
 -16.250  -1.1758   0.06146   0.05623  -0.0439   1.0000   0.0735
 -16.000  -1.1906   0.05637   0.05100  -0.0466   1.0000   0.0756
 -15.750  -1.2079   0.05119   0.04558  -0.0494   1.0000   0.0778
 -15.500  -1.2140   0.04783   0.04222  -0.0503   1.0000   0.0804
 -15.250  -1.2194   0.04474   0.03909  -0.0513   1.0000   0.0830
 -15.000  -1.2258   0.04177   0.03599  -0.0518   1.0000   0.0858
 -14.750  -1.2347   0.03891   0.03290  -0.0518   1.0000   0.0886
 -14.500  -1.2356   0.03689   0.03091  -0.0510   1.0000   0.0917
 -14.250  -1.2358   0.03529   0.02926  -0.0498   1.0000   0.0949
 -14.000  -1.2369   0.03376   0.02759  -0.0481   1.0000   0.0982
 -13.750  -1.2384   0.03228   0.02593  -0.0460   1.0000   0.1016
 -13.500  -1.2329   0.03131   0.02502  -0.0439   1.0000   0.1050
 -13.250  -1.2293   0.03049   0.02412  -0.0414   1.0000   0.1088
 -13.000  -1.2292   0.02960   0.02301  -0.0381   1.0000   0.1124
 -12.750  -1.2213   0.02878   0.02226  -0.0355   1.0000   0.1162
 -12.500  -1.2137   0.02834   0.02180  -0.0327   1.0000   0.1201
 -12.250  -1.2065   0.02775   0.02102  -0.0299   1.0000   0.1245
 -12.000  -1.1943   0.02707   0.02035  -0.0278   1.0000   0.1288
 -11.750  -1.1804   0.02682   0.02010  -0.0257   1.0000   0.1332
 -11.500  -1.1700   0.02638   0.01946  -0.0230   1.0000   0.1380
 -11.250  -1.1544   0.02579   0.01891  -0.0212   1.0000   0.1424
 -11.000  -1.1379   0.02556   0.01869  -0.0193   1.0000   0.1467
 -10.750  -1.1248   0.02515   0.01809  -0.0169   1.0000   0.1513
 -10.500  -1.1085   0.02450   0.01740  -0.0151   1.0000   0.1555
 -10.250  -1.0899   0.02427   0.01721  -0.0135   1.0000   0.1595
 -10.000  -1.0738   0.02392   0.01675  -0.0115   1.0000   0.1641
  -9.750  -1.0586   0.02335   0.01601  -0.0093   1.0000   0.1683
  -9.500  -1.0382   0.02297   0.01572  -0.0080   1.0000   0.1722
  -9.250  -1.0198   0.02271   0.01542  -0.0063   1.0000   0.1765
  -9.000  -1.0038   0.02234   0.01485  -0.0041   1.0000   0.1811
  -8.750  -0.9840   0.02176   0.01430  -0.0027   1.0000   0.1851
  -8.500  -0.9638   0.02149   0.01405  -0.0012   1.0000   0.1891
  -8.250  -0.9453   0.02118   0.01364   0.0005   1.0000   0.1938
  -8.000  -0.9274   0.02073   0.01302   0.0024   1.0000   0.1981
  -7.750  -0.9059   0.02026   0.01265   0.0035   1.0000   0.2020
  -7.500  -0.8855   0.01997   0.01234   0.0050   1.0000   0.2063
  -7.250  -0.8664   0.01967   0.01190   0.0067   1.0000   0.2111
  -7.000  -0.8458   0.01913   0.01132   0.0080   1.0000   0.2152
  -6.750  -0.8243   0.01879   0.01104   0.0092   1.0000   0.2193
  -6.500  -0.8036   0.01851   0.01071   0.0106   1.0000   0.2239
  -6.250  -0.7836   0.01827   0.01031   0.0122   1.0000   0.2285
  -6.000  -0.7614   0.01771   0.00983   0.0132   1.0000   0.2326
  -5.750  -0.7399   0.01742   0.00957   0.0145   1.0000   0.2370
  -5.500  -0.7188   0.01718   0.00926   0.0158   1.0000   0.2420
  -5.250  -0.6974   0.01682   0.00884   0.0171   1.0000   0.2465
  -5.000  -0.6754   0.01647   0.00857   0.0181   1.0000   0.2507
  -4.750  -0.6538   0.01624   0.00834   0.0193   1.0000   0.2555
  -4.500  -0.6325   0.01608   0.00809   0.0206   1.0000   0.2607
  -4.250  -0.6106   0.01571   0.00780   0.0217   1.0000   0.2654
  -4.000  -0.5890   0.01551   0.00764   0.0228   1.0000   0.2702
  -3.750  -0.5678   0.01536   0.00746   0.0240   1.0000   0.2755
  -3.500  -0.5280   0.01513   0.00729   0.0215   0.9952   0.2820
  -3.250  -0.4790   0.01498   0.00720   0.0172   0.9869   0.2901
  -3.000  -0.4296   0.01470   0.00697   0.0130   0.9788   0.2978
  -2.750  -0.3808   0.01444   0.00679   0.0089   0.9697   0.3068
  -2.500  -0.3367   0.01408   0.00651   0.0059   0.9591   0.3157
  -2.250  -0.2890   0.01374   0.00623   0.0023   0.9486   0.3259
  -2.000  -0.2383   0.01325   0.00590  -0.0018   0.9383   0.3371
  -1.750  -0.1983   0.01281   0.00555  -0.0037   0.9222   0.3491
  -1.500  -0.1662   0.01243   0.00524  -0.0038   0.8969   0.3617
  -1.250  -0.1305   0.01196   0.00488  -0.0046   0.8609   0.3764
  -1.000  -0.0886   0.01154   0.00443  -0.0065   0.7973   0.3963
  -0.750  -0.0600   0.01143   0.00413  -0.0057   0.7127   0.4170
  -0.500  -0.0391   0.01152   0.00400  -0.0038   0.6339   0.4410
  -0.250  -0.0196   0.01162   0.00393  -0.0019   0.5665   0.4711
   0.000   0.0000   0.01166   0.00391   0.0000   0.5122   0.5122
   0.250   0.0196   0.01162   0.00393   0.0019   0.4711   0.5663
   0.500   0.0391   0.01152   0.00400   0.0038   0.4408   0.6339
   0.750   0.0600   0.01143   0.00413   0.0057   0.4169   0.7127
   1.000   0.0886   0.01154   0.00443   0.0065   0.3963   0.7974
   1.250   0.1304   0.01196   0.00488   0.0047   0.3765   0.8608
   1.500   0.1662   0.01243   0.00523   0.0038   0.3617   0.8968
   1.750   0.1982   0.01280   0.00555   0.0037   0.3492   0.9222
   2.000   0.2382   0.01325   0.00590   0.0018   0.3373   0.9382
   2.250   0.2890   0.01373   0.00623  -0.0023   0.3258   0.9486
   2.500   0.3366   0.01407   0.00651  -0.0059   0.3157   0.9591
   2.750   0.3810   0.01444   0.00679  -0.0090   0.3068   0.9697
   3.000   0.4295   0.01470   0.00696  -0.0129   0.2977   0.9789
   3.250   0.4793   0.01497   0.00719  -0.0173   0.2900   0.9870
   3.500   0.5283   0.01513   0.00729  -0.0215   0.2820   0.9953
   3.750   0.5677   0.01536   0.00746  -0.0240   0.2754   1.0000
   4.000   0.5889   0.01551   0.00764  -0.0228   0.2702   1.0000
   4.250   0.6105   0.01571   0.00780  -0.0217   0.2654   1.0000
   4.500   0.6325   0.01608   0.00809  -0.0206   0.2607   1.0000
   4.750   0.6537   0.01624   0.00834  -0.0193   0.2556   1.0000
   5.000   0.6753   0.01647   0.00856  -0.0181   0.2507   1.0000
   5.250   0.6973   0.01682   0.00884  -0.0170   0.2466   1.0000
   5.500   0.7187   0.01717   0.00925  -0.0158   0.2420   1.0000
   5.750   0.7398   0.01741   0.00956  -0.0145   0.2370   1.0000
   6.000   0.7614   0.01770   0.00983  -0.0132   0.2326   1.0000
   6.250   0.7836   0.01827   0.01031  -0.0122   0.2285   1.0000
   6.500   0.8035   0.01851   0.01071  -0.0106   0.2240   1.0000
   6.750   0.8242   0.01879   0.01104  -0.0092   0.2193   1.0000
   7.000   0.8457   0.01913   0.01133  -0.0080   0.2153   1.0000
   7.250   0.8664   0.01968   0.01190  -0.0067   0.2111   1.0000
   7.500   0.8855   0.01997   0.01234  -0.0050   0.2063   1.0000
   7.750   0.9058   0.02026   0.01265  -0.0035   0.2020   1.0000
   8.000   0.9274   0.02072   0.01301  -0.0024   0.1982   1.0000
   8.250   0.9453   0.02118   0.01364  -0.0005   0.1938   1.0000
   8.500   0.9638   0.02148   0.01404   0.0012   0.1891   1.0000
   8.750   0.9840   0.02175   0.01429   0.0027   0.1851   1.0000
   9.000   1.0038   0.02234   0.01485   0.0041   0.1811   1.0000
   9.250   1.0197   0.02270   0.01541   0.0063   0.1766   1.0000
   9.500   1.0382   0.02298   0.01572   0.0080   0.1722   1.0000
   9.750   1.0585   0.02335   0.01600   0.0093   0.1683   1.0000
  10.000   1.0738   0.02393   0.01676   0.0114   0.1641   1.0000
  10.250   1.0899   0.02427   0.01722   0.0135   0.1595   1.0000
  10.500   1.1085   0.02450   0.01740   0.0151   0.1555   1.0000
  10.750   1.1249   0.02515   0.01809   0.0169   0.1514   1.0000
  11.000   1.1380   0.02557   0.01870   0.0193   0.1467   1.0000
  11.250   1.1545   0.02579   0.01890   0.0212   0.1424   1.0000
  11.500   1.1701   0.02638   0.01947   0.0230   0.1380   1.0000
  11.750   1.1805   0.02682   0.02010   0.0256   0.1332   1.0000
  12.000   1.1944   0.02706   0.02033   0.0277   0.1288   1.0000
  12.250   1.2066   0.02773   0.02101   0.0298   0.1245   1.0000
  12.500   1.2139   0.02832   0.02178   0.0327   0.1200   1.0000
  12.750   1.2217   0.02876   0.02224   0.0355   0.1161   1.0000
  13.000   1.2296   0.02959   0.02301   0.0380   0.1123   1.0000
  13.250   1.2298   0.03048   0.02411   0.0413   0.1088   1.0000
  13.500   1.2335   0.03130   0.02501   0.0438   0.1050   1.0000
  13.750   1.2392   0.03229   0.02592   0.0459   0.1015   1.0000
  14.000   1.2376   0.03377   0.02760   0.0481   0.0982   1.0000
  14.250   1.2364   0.03528   0.02925   0.0497   0.0947   1.0000
  14.500   1.2364   0.03688   0.03088   0.0509   0.0916   1.0000
  14.750   1.2353   0.03891   0.03291   0.0517   0.0885   1.0000
  15.000   1.2270   0.04174   0.03597   0.0517   0.0858   1.0000
  15.250   1.2205   0.04471   0.03906   0.0511   0.0829   1.0000
  15.500   1.2153   0.04777   0.04215   0.0502   0.0803   1.0000
  15.750   1.2084   0.05124   0.04564   0.0491   0.0777   1.0000
  16.000   1.1925   0.05627   0.05089   0.0465   0.0757   1.0000
  16.250   1.1777   0.06136   0.05613   0.0438   0.0735   1.0000
  16.500   1.1657   0.06614   0.06098   0.0411   0.0712   1.0000
  16.750   1.1655   0.06892   0.06363   0.0404   0.0684   1.0000
  17.000   1.1396   0.07622   0.07117   0.0360   0.0672   1.0000
  17.250   1.1148   0.08358   0.07873   0.0317   0.0658   1.0000
  17.500   1.0906   0.09111   0.08641   0.0273   0.0642   1.0000
  17.750   1.0789   0.09659   0.09193   0.0243   0.0620   1.0000
  18.000   1.0896   0.09783   0.09302   0.0243   0.0591   1.0000
  18.250   1.0522   0.10837   0.10380   0.0179   0.0583   1.0000
  18.500   0.9936   0.12357   0.11929   0.0086   0.0579   1.0000
<< Back to E474 (14.09%) (e474-il)

Polar data table (+)

Polar graphs


<< Back to E474 (14.09%) (e474-il)