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GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 441 AIRFOIL (goe441-il)
Reynolds number: 100,000
Max Cl/Cd: 45.62 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe441-il-100000.txt
Download as CSV file: xf-goe441-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 441 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000   0.0837   0.10209   0.09731  -0.0984   0.9168   0.1151
  -7.750   0.0739   0.10206   0.09730  -0.1052   0.9055   0.1188
  -7.500   0.0730   0.09950   0.09478  -0.1058   0.8931   0.1197
  -7.250   0.1258   0.09271   0.08793  -0.1076   0.8918   0.1221
  -7.000   0.1570   0.08871   0.08390  -0.1111   0.8872   0.1257
  -6.750   0.1609   0.08685   0.08205  -0.1111   0.8737   0.1294
  -6.500   0.1336   0.08781   0.08306  -0.1207   0.8541   0.1335
  -6.250   0.1717   0.08164   0.07684  -0.1160   0.8517   0.1353
  -6.000   0.1905   0.07893   0.07413  -0.1138   0.8397   0.1386
  -5.750   0.2085   0.07633   0.07147  -0.1187   0.8308   0.1466
  -5.500   0.2156   0.07338   0.06851  -0.1234   0.8156   0.1503
  -5.250   0.2325   0.07078   0.06589  -0.1202   0.8021   0.1528
  -5.000   0.2529   0.06822   0.06325  -0.1213   0.7899   0.1584
  -4.750   0.2755   0.06458   0.05950  -0.1308   0.7773   0.1669
  -4.500   0.2896   0.06259   0.05748  -0.1277   0.7619   0.1700
  -4.250   0.3193   0.05926   0.05400  -0.1395   0.7467   0.1834
  -4.000   0.3353   0.05731   0.05198  -0.1349   0.7358   0.1867
  -3.750   0.4340   0.03650   0.02985  -0.1795   0.7251   0.1207
  -3.500   0.4815   0.03202   0.02449  -0.1869   0.7132   0.1191
  -3.250   0.5114   0.03067   0.02316  -0.1876   0.7028   0.1236
  -3.000   0.5440   0.02893   0.02105  -0.1897   0.6902   0.1272
  -2.750   0.5861   0.02687   0.01825  -0.1931   0.6817   0.1343
  -2.500   0.6115   0.02640   0.01785  -0.1929   0.6706   0.1415
  -2.250   0.6470   0.02536   0.01641  -0.1945   0.6629   0.1520
  -2.000   0.6750   0.02508   0.01596  -0.1947   0.6529   0.1639
  -1.750   0.7081   0.02452   0.01527  -0.1955   0.6464   0.1778
  -1.500   0.7336   0.02434   0.01510  -0.1954   0.6371   0.1911
  -1.250   0.7655   0.02394   0.01454  -0.1961   0.6307   0.2068
  -1.000   0.7940   0.02379   0.01430  -0.1963   0.6239   0.2221
  -0.750   0.8226   0.02368   0.01409  -0.1965   0.6170   0.2382
  -0.500   0.8549   0.02337   0.01367  -0.1972   0.6116   0.2566
  -0.250   0.8798   0.02338   0.01381  -0.1969   0.6047   0.2750
   0.000   0.9084   0.02326   0.01378  -0.1971   0.5988   0.3006
   0.250   0.9407   0.02311   0.01372  -0.1978   0.5943   0.3457
   0.500   0.9662   0.02339   0.01426  -0.1975   0.5885   0.4152
   0.750   0.9923   0.02364   0.01469  -0.1971   0.5828   0.4950
   1.000   1.0208   0.02372   0.01482  -0.1969   0.5781   0.5665
   1.250   1.0466   0.02400   0.01516  -0.1962   0.5735   0.6254
   1.500   1.0666   0.02446   0.01580  -0.1948   0.5683   0.6744
   1.750   1.0897   0.02472   0.01613  -0.1938   0.5635   0.7306
   2.000   1.1135   0.02464   0.01612  -0.1925   0.5595   0.8088
   2.250   1.1350   0.02488   0.01643  -0.1914   0.5551   1.0000
   2.500   1.1592   0.02574   0.01723  -0.1915   0.5498   1.0000
   2.750   1.1872   0.02637   0.01773  -0.1919   0.5451   1.0000
   3.000   1.2191   0.02687   0.01800  -0.1927   0.5411   1.0000
   3.250   1.2445   0.02771   0.01876  -0.1927   0.5368   1.0000
   3.500   1.2626   0.02873   0.01984  -0.1917   0.5316   1.0000
   3.750   1.2865   0.02951   0.02057  -0.1913   0.5270   1.0000
   4.000   1.3161   0.03007   0.02099  -0.1917   0.5230   1.0000
   4.250   1.3448   0.03088   0.02166  -0.1921   0.5192   1.0000
   4.500   1.3533   0.03232   0.02329  -0.1897   0.5139   1.0000
   4.750   1.3728   0.03332   0.02432  -0.1888   0.5092   1.0000
   5.000   1.3999   0.03395   0.02487  -0.1889   0.5050   1.0000
   5.250   1.4332   0.03452   0.02527  -0.1898   0.5015   1.0000
   5.500   1.4346   0.03644   0.02742  -0.1866   0.4964   1.0000
   5.750   1.4412   0.03810   0.02921  -0.1841   0.4912   1.0000
   6.000   1.4657   0.03882   0.02990  -0.1838   0.4870   1.0000
   6.250   1.4994   0.03918   0.03015  -0.1846   0.4835   1.0000
   6.500   1.5098   0.04092   0.03198  -0.1827   0.4794   1.0000
   6.750   1.4723   0.04498   0.03640  -0.1752   0.4727   1.0000
   7.000   1.4880   0.04615   0.03759  -0.1739   0.4684   1.0000
   7.250   1.5316   0.04579   0.03711  -0.1757   0.4653   1.0000
   7.500   1.5804   0.04552   0.03669  -0.1783   0.4625   1.0000
   7.750   1.3088   0.06837   0.06040  -0.1541   0.4448   1.0000
   8.000   1.3757   0.06427   0.05620  -0.1550   0.4448   1.0000
   8.250   1.4500   0.06030   0.05212  -0.1572   0.4445   1.0000
   8.500   1.5369   0.05649   0.04817  -0.1618   0.4437   1.0000
   8.750   0.9692   0.13173   0.12455  -0.1587   0.4118   1.0000
   9.000   0.9899   0.13361   0.12640  -0.1584   0.4099   1.0000
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