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E63 (4.25%) (e63-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E63 (4.25%) (e63-il)
Reynolds number: 1,000,000
Max Cl/Cd: 235.17 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e63-il-1000000.txt
Download as CSV file: xf-e63-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E63  (4.25%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1832   0.08151   0.07995  -0.0484   0.9855   0.0048
  -7.500  -0.1700   0.07771   0.07615  -0.0516   0.9849   0.0049
  -7.250  -0.1679   0.07487   0.07333  -0.0516   0.9799   0.0050
  -7.000  -0.1577   0.07133   0.06979  -0.0538   0.9778   0.0050
  -6.750  -0.1463   0.06763   0.06609  -0.0567   0.9761   0.0050
  -6.500  -0.1336   0.06385   0.06232  -0.0599   0.9748   0.0050
  -6.250  -0.1180   0.05986   0.05832  -0.0639   0.9736   0.0051
  -6.000  -0.1135   0.05694   0.05542  -0.0646   0.9667   0.0051
  -5.750  -0.0936   0.05261   0.05108  -0.0699   0.9647   0.0051
  -5.500  -0.0702   0.04811   0.04658  -0.0760   0.9634   0.0051
  -5.250  -0.0432   0.04335   0.04181  -0.0832   0.9625   0.0051
  -4.250   0.0270   0.04700   0.04525  -0.1110   0.9572   0.0062
  -4.000   0.0722   0.04268   0.04087  -0.1202   0.9555   0.0070
  -3.750   0.1274   0.03805   0.03615  -0.1307   0.9547   0.0085
  -3.500   0.1803   0.03399   0.03198  -0.1394   0.9541   0.0090
  -3.250   0.2346   0.02943   0.02726  -0.1481   0.9538   0.0091
  -3.000   0.2878   0.02508   0.02269  -0.1558   0.9536   0.0091
  -2.750   0.3388   0.02122   0.01856  -0.1624   0.9535   0.0091
  -1.250   0.5998   0.00822   0.00387  -0.1852   0.9520   0.0085
  -1.000   0.6389   0.00737   0.00288  -0.1876   0.9512   0.0105
  -0.750   0.6751   0.00696   0.00245  -0.1893   0.9501   0.0137
  -0.500   0.7002   0.00673   0.00217  -0.1885   0.9437   0.0152
  -0.250   0.7363   0.00608   0.00195  -0.1905   0.9406   0.2074
   0.000   0.7753   0.00528   0.00200  -0.1935   0.9383   0.5852
   0.250   0.8063   0.00477   0.00202  -0.1942   0.9319   0.8242
   0.500   0.8399   0.00428   0.00172  -0.1952   0.9248   1.0000
   0.750   0.8813   0.00414   0.00154  -0.1982   0.9133   1.0000
   1.000   0.9300   0.00406   0.00139  -0.2029   0.8979   1.0000
   1.250   0.9689   0.00412   0.00132  -0.2053   0.8693   1.0000
   1.500   0.9981   0.00435   0.00135  -0.2055   0.8291   1.0000
   1.750   1.0209   0.00470   0.00146  -0.2042   0.7809   1.0000
   2.000   1.0411   0.00513   0.00162  -0.2024   0.7259   1.0000
   2.250   1.0585   0.00575   0.00188  -0.2000   0.6472   1.0000
   2.500   1.0748   0.00663   0.00221  -0.1976   0.5349   1.0000
   2.750   1.0957   0.00732   0.00250  -0.1962   0.4522   1.0000
   3.000   1.1158   0.00818   0.00286  -0.1949   0.3516   1.0000
   3.250   1.1370   0.00898   0.00323  -0.1937   0.2643   1.0000
   3.500   1.1589   0.00971   0.00360  -0.1928   0.1922   1.0000
   3.750   1.1808   0.01048   0.00405  -0.1917   0.1241   1.0000
   4.000   1.2018   0.01140   0.00458  -0.1906   0.0536   1.0000
   4.250   1.2240   0.01220   0.00515  -0.1894   0.0131   1.0000
   4.500   1.2488   0.01259   0.00561  -0.1888   0.0114   1.0000
   4.750   1.2733   0.01303   0.00611  -0.1880   0.0106   1.0000
   5.000   1.2974   0.01353   0.00671  -0.1872   0.0102   1.0000
   5.250   1.3211   0.01407   0.00733  -0.1863   0.0096   1.0000
   5.500   1.3443   0.01470   0.00805  -0.1853   0.0094   1.0000
   5.750   1.3668   0.01543   0.00888  -0.1841   0.0091   1.0000
   6.000   1.3885   0.01627   0.00982  -0.1828   0.0088   1.0000
   6.250   1.4086   0.01739   0.01105  -0.1812   0.0083   1.0000
   6.500   1.4254   0.01930   0.01317  -0.1788   0.0077   1.0000
   6.750   1.4427   0.02183   0.01592  -0.1766   0.0069   1.0000
   7.000   1.4656   0.02248   0.01665  -0.1757   0.0066   1.0000
   7.250   1.4871   0.02379   0.01810  -0.1744   0.0063   1.0000
   7.500   1.5081   0.02529   0.01975  -0.1730   0.0059   1.0000
   7.750   1.5294   0.02586   0.02041  -0.1720   0.0051   1.0000
   8.000   1.5503   0.02617   0.02075  -0.1711   0.0045   1.0000
   8.250   1.5688   0.02708   0.02168  -0.1699   0.0040   1.0000
   8.500   1.5791   0.03150   0.02656  -0.1667   0.0034   1.0000
   8.750   1.5988   0.03204   0.02726  -0.1654   0.0031   1.0000
   9.000   1.6137   0.03405   0.02952  -0.1631   0.0028   1.0000
   9.250   1.6305   0.03491   0.03049  -0.1615   0.0024   1.0000
   9.500   1.6400   0.03751   0.03337  -0.1586   0.0023   1.0000
   9.750   1.6590   0.03709   0.03292  -0.1576   0.0020   1.0000
  10.000   1.6775   0.03667   0.03246  -0.1565   0.0019   1.0000
  10.250   1.6517   0.04347   0.03988  -0.1485   0.0016   1.0000
  10.500   1.6647   0.04370   0.04018  -0.1461   0.0014   1.0000
  10.750   1.6478   0.04787   0.04471  -0.1398   0.0014   1.0000
  11.000   1.6296   0.05224   0.04940  -0.1342   0.0014   1.0000
  11.250   1.6013   0.05808   0.05558  -0.1286   0.0013   1.0000
  11.500   1.5757   0.06389   0.06168  -0.1248   0.0013   1.0000
  11.750   1.5452   0.07078   0.06883  -0.1227   0.0013   1.0000
  12.000   1.5238   0.07684   0.07508  -0.1225   0.0014   1.0000
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