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E203 (13.64%) (e203-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E203 (13.64%) (e203-il)
Reynolds number: 50,000
Max Cl/Cd: 32.01 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e203-il-50000.txt
Download as CSV file: xf-e203-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E203  (13.64%)                                  
  
 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  -0.3669   0.10620   0.09933  -0.0285   1.0000   0.3014
  -9.000  -0.4708   0.08220   0.07574  -0.0517   1.0000   0.1393
  -8.750  -0.4866   0.07694   0.07057  -0.0529   1.0000   0.1340
  -8.500  -0.5688   0.06863   0.06227  -0.0565   1.0000   0.1225
  -8.250  -0.5768   0.06488   0.05852  -0.0551   1.0000   0.1210
  -8.000  -0.5905   0.06111   0.05469  -0.0535   1.0000   0.1193
  -7.750  -0.6048   0.05730   0.05071  -0.0519   1.0000   0.1180
  -7.500  -0.6153   0.05358   0.04673  -0.0502   1.0000   0.1168
  -7.250  -0.6199   0.05016   0.04299  -0.0485   1.0000   0.1170
  -7.000  -0.6194   0.04701   0.03947  -0.0470   1.0000   0.1180
  -6.750  -0.6146   0.04400   0.03603  -0.0455   1.0000   0.1196
  -6.500  -0.6058   0.04114   0.03265  -0.0443   1.0000   0.1214
  -6.250  -0.5930   0.03854   0.02947  -0.0430   1.0000   0.1234
  -6.000  -0.5773   0.03633   0.02730  -0.0418   1.0000   0.1282
  -5.750  -0.5606   0.03459   0.02517  -0.0407   1.0000   0.1365
  -5.500  -0.5436   0.03295   0.02353  -0.0396   1.0000   0.1479
  -5.250  -0.5255   0.03129   0.02177  -0.0383   1.0000   0.1641
  -5.000  -0.5087   0.02977   0.02043  -0.0371   1.0000   0.1917
  -4.750  -0.4924   0.02830   0.01921  -0.0359   1.0000   0.2396
  -4.500  -0.4783   0.02726   0.01882  -0.0343   1.0000   0.3093
  -4.250  -0.4652   0.02728   0.01935  -0.0316   1.0000   0.3873
  -4.000  -0.4531   0.02784   0.02014  -0.0283   1.0000   0.4537
  -3.750  -0.4422   0.02844   0.02088  -0.0246   1.0000   0.5049
  -3.500  -0.4313   0.02889   0.02138  -0.0209   1.0000   0.5490
  -3.250  -0.4200   0.02918   0.02164  -0.0176   1.0000   0.5893
  -3.000  -0.4094   0.02940   0.02186  -0.0141   1.0000   0.6230
  -2.750  -0.3987   0.02952   0.02193  -0.0108   1.0000   0.6544
  -2.250  -0.3502   0.03039   0.02262  -0.0086   0.9855   0.7219
  -2.000  -0.3266   0.03065   0.02275  -0.0078   0.9772   0.7522
  -1.750  -0.3007   0.03097   0.02294  -0.0074   0.9695   0.7816
  -1.500  -0.2792   0.03105   0.02291  -0.0066   0.9613   0.8090
  -1.250  -0.2551   0.03122   0.02297  -0.0063   0.9537   0.8372
  -1.000  -0.2308   0.03135   0.02300  -0.0061   0.9461   0.8656
  -0.750  -0.2006   0.03158   0.02315  -0.0072   0.9384   0.8963
  -0.500  -0.1445   0.03224   0.02366  -0.0134   0.9305   0.9301
  -0.250  -0.0652   0.03316   0.02438  -0.0249   0.9218   0.9619
   0.000   0.0409   0.03431   0.02526  -0.0418   0.9133   0.9921
   0.250   0.0325   0.03387   0.02477  -0.0400   0.9051   1.0000
   0.500   0.0487   0.03399   0.02470  -0.0419   0.8976   1.0000
   0.750   0.0685   0.03444   0.02495  -0.0437   0.8900   1.0000
   1.000   0.1058   0.03533   0.02561  -0.0477   0.8826   1.0000
   1.250   0.1263   0.03608   0.02620  -0.0487   0.8750   1.0000
   1.500   0.1627   0.03714   0.02708  -0.0518   0.8680   1.0000
   1.750   0.1779   0.03799   0.02781  -0.0516   0.8608   1.0000
   2.000   0.2160   0.03916   0.02885  -0.0547   0.8536   1.0000
   2.250   0.2258   0.04008   0.02970  -0.0536   0.8466   1.0000
   2.500   0.2641   0.04129   0.03083  -0.0565   0.8389   1.0000
   2.750   0.2713   0.04233   0.03182  -0.0551   0.8322   1.0000
   3.000   0.3075   0.04357   0.03301  -0.0575   0.8241   1.0000
   3.250   0.3147   0.04473   0.03414  -0.0562   0.8173   1.0000
   3.500   0.3527   0.04603   0.03543  -0.0588   0.8085   1.0000
   3.750   0.3563   0.04728   0.03666  -0.0571   0.8016   1.0000
   4.000   0.3899   0.04861   0.03800  -0.0589   0.7920   1.0000
   4.250   0.3983   0.04994   0.03936  -0.0579   0.7840   1.0000
   4.500   0.4228   0.05133   0.04077  -0.0587   0.7742   1.0000
   4.750   0.4602   0.05265   0.04214  -0.0607   0.7628   1.0000
   5.000   0.4608   0.05416   0.04367  -0.0589   0.7536   1.0000
   5.250   0.4827   0.05558   0.04517  -0.0592   0.7418   1.0000
   5.500   0.5092   0.05696   0.04662  -0.0599   0.7290   1.0000
   5.750   0.5369   0.05828   0.04803  -0.0605   0.7153   1.0000
   6.000   0.5650   0.05956   0.04942  -0.0611   0.7012   1.0000
   6.250   0.5913   0.06082   0.05078  -0.0614   0.6865   1.0000
   6.500   0.6122   0.06211   0.05219  -0.0611   0.6710   1.0000
   6.750   0.6307   0.06348   0.05366  -0.0606   0.6551   1.0000
   7.000   0.6467   0.06490   0.05521  -0.0599   0.6383   1.0000
   7.250   0.6638   0.06627   0.05670  -0.0591   0.6206   1.0000
   7.500   0.6871   0.06733   0.05791  -0.0586   0.6021   1.0000
   7.750   0.7233   0.06761   0.05840  -0.0584   0.5833   1.0000
   8.000   0.7531   0.06799   0.05899  -0.0576   0.5639   1.0000
   8.250   0.7636   0.06942   0.06055  -0.0562   0.5435   1.0000
   8.500   0.8135   0.06774   0.05917  -0.0550   0.5228   1.0000
   8.750   0.8298   0.06843   0.06005  -0.0532   0.5011   1.0000
   9.000   0.9047   0.06258   0.05468  -0.0504   0.4782   1.0000
   9.250   1.1386   0.03739   0.03040  -0.0479   0.4155   1.0000
   9.500   1.1514   0.03615   0.02897  -0.0431   0.3655   1.0000
   9.750   1.1583   0.03619   0.02844  -0.0385   0.3140   1.0000
  10.000   1.1551   0.03780   0.02967  -0.0341   0.2732   1.0000
  10.250   1.1559   0.03997   0.03148  -0.0307   0.2361   1.0000
  10.500   1.1601   0.04234   0.03356  -0.0279   0.2038   1.0000
  10.750   1.1669   0.04488   0.03588  -0.0257   0.1760   1.0000
  11.000   1.1773   0.04757   0.03841  -0.0239   0.1517   1.0000
  11.250   1.1848   0.05031   0.04113  -0.0221   0.1331   1.0000
  11.500   1.2006   0.05333   0.04410  -0.0210   0.1172   1.0000
  11.750   1.2079   0.05679   0.04781  -0.0194   0.1080   1.0000
  12.000   1.2232   0.06038   0.05144  -0.0187   0.0995   1.0000
  12.250   1.2136   0.06391   0.05539  -0.0163   0.0969   1.0000
  12.500   1.2051   0.06776   0.05958  -0.0145   0.0948   1.0000
  12.750   1.1958   0.07176   0.06386  -0.0132   0.0931   1.0000
  13.000   1.2149   0.07619   0.06819  -0.0132   0.0881   1.0000
  13.250   1.1944   0.08051   0.07281  -0.0121   0.0880   1.0000
  13.500   1.1731   0.08531   0.07788  -0.0118   0.0880   1.0000
  13.750   1.1502   0.09066   0.08345  -0.0123   0.0882   1.0000
  14.000   1.0540   0.10270   0.09612  -0.0193   0.0978   1.0000
  14.250   1.0251   0.11120   0.10472  -0.0234   0.0994   1.0000
  14.500   1.0026   0.11981   0.11339  -0.0277   0.1006   1.0000
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