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GOE 404 AIRFOIL (goe404-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 404 AIRFOIL (goe404-il)
Reynolds number: 100,000
Max Cl/Cd: 45.23 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe404-il-100000.txt
Download as CSV file: xf-goe404-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 404 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2619   0.09986   0.09533  -0.0249   1.0000   0.1082
  -7.500  -0.2883   0.10016   0.09579  -0.0205   1.0000   0.1088
  -7.250  -0.2998   0.09855   0.09423  -0.0287   0.9898   0.1117
  -7.000  -0.2728   0.09232   0.08798  -0.0395   0.9796   0.1136
  -6.750  -0.2402   0.08854   0.08420  -0.0386   0.9741   0.1161
  -6.500  -0.2059   0.08418   0.07982  -0.0457   0.9661   0.1207
  -6.250  -0.1852   0.07836   0.07381  -0.0658   0.9471   0.1269
  -6.000  -0.1528   0.07427   0.06980  -0.0651   0.9414   0.1288
  -5.750  -0.1143   0.07038   0.06589  -0.0693   0.9364   0.1330
  -5.500  -0.0898   0.06579   0.06098  -0.0827   0.9202   0.1423
  -5.250  -0.0660   0.06242   0.05772  -0.0817   0.9099   0.1444
  -5.000  -0.0311   0.05977   0.05463  -0.0909   0.8997   0.1581
  -4.750  -0.0149   0.05607   0.05113  -0.0885   0.8867   0.1603
  -4.500   0.0120   0.05482   0.04960  -0.0915   0.8739   0.1742
  -4.250   0.0336   0.05055   0.04540  -0.0916   0.8642   0.1778
  -4.000   0.0524   0.04839   0.04327  -0.0905   0.8508   0.1832
  -3.750   0.0762   0.04580   0.04047  -0.0920   0.8395   0.1967
  -3.500   0.0990   0.04382   0.03829  -0.0926   0.8270   0.2131
  -3.250   0.1183   0.04175   0.03627  -0.0911   0.8135   0.2217
  -3.000   0.1652   0.03268   0.02544  -0.0965   0.8060   0.1279
  -2.750   0.1904   0.03066   0.02286  -0.0954   0.7918   0.1257
  -2.500   0.2144   0.02904   0.02131  -0.0948   0.7785   0.1309
  -2.250   0.2430   0.02751   0.01943  -0.0941   0.7673   0.1362
  -2.000   0.2695   0.02609   0.01752  -0.0931   0.7529   0.1425
  -1.750   0.2946   0.02522   0.01666  -0.0923   0.7380   0.1507
  -1.500   0.3219   0.02432   0.01540  -0.0915   0.7240   0.1601
  -1.000   0.3754   0.02311   0.01387  -0.0900   0.6955   0.1787
  -0.750   0.4014   0.02271   0.01340  -0.0893   0.6805   0.1868
  -0.500   0.4291   0.02246   0.01286  -0.0885   0.6669   0.1929
  -0.250   0.4565   0.02182   0.01218  -0.0880   0.6543   0.1993
   0.000   0.4823   0.02160   0.01191  -0.0872   0.6399   0.2055
   0.250   0.5095   0.02140   0.01158  -0.0867   0.6281   0.2119
   0.500   0.5364   0.02105   0.01125  -0.0861   0.6172   0.2187
   0.750   0.5622   0.02100   0.01120  -0.0854   0.6057   0.2276
   1.000   0.5894   0.02070   0.01091  -0.0848   0.5968   0.2385
   1.250   0.6144   0.02067   0.01096  -0.0841   0.5859   0.2515
   1.500   0.6422   0.02045   0.01075  -0.0837   0.5779   0.2768
   1.750   0.6604   0.01888   0.01107  -0.0816   0.5690   0.7927
   2.000   0.7136   0.01900   0.01086  -0.0857   0.5604   1.0000
   2.250   0.7385   0.01946   0.01119  -0.0851   0.5528   1.0000
   2.500   0.7636   0.01986   0.01147  -0.0845   0.5454   1.0000
   2.750   0.7919   0.02015   0.01152  -0.0841   0.5396   1.0000
   3.000   0.8140   0.02068   0.01208  -0.0833   0.5310   1.0000
   3.250   0.8407   0.02095   0.01221  -0.0828   0.5242   1.0000
   3.500   0.8657   0.02139   0.01257  -0.0822   0.5173   1.0000
   3.750   0.8898   0.02178   0.01293  -0.0815   0.5094   1.0000
   4.000   0.9186   0.02199   0.01293  -0.0812   0.5035   1.0000
   4.250   0.9397   0.02257   0.01360  -0.0802   0.4954   1.0000
   4.500   0.9659   0.02285   0.01379  -0.0797   0.4886   1.0000
   4.750   0.9922   0.02325   0.01410  -0.0793   0.4826   1.0000
   5.000   1.0140   0.02376   0.01467  -0.0784   0.4746   1.0000
   5.250   1.0423   0.02395   0.01470  -0.0781   0.4683   1.0000
   5.500   1.0639   0.02459   0.01541  -0.0772   0.4614   1.0000
   5.750   1.0875   0.02508   0.01593  -0.0765   0.4548   1.0000
   6.000   1.1168   0.02534   0.01603  -0.0765   0.4493   1.0000
   6.250   1.1353   0.02610   0.01695  -0.0752   0.4419   1.0000
   6.500   1.1601   0.02647   0.01730  -0.0746   0.4350   1.0000
   6.750   1.1873   0.02686   0.01759  -0.0744   0.4287   1.0000
   7.000   1.2051   0.02755   0.01844  -0.0730   0.4205   1.0000
   7.250   1.2336   0.02777   0.01855  -0.0728   0.4139   1.0000
   7.500   1.2514   0.02853   0.01945  -0.0715   0.4058   1.0000
   7.750   1.2758   0.02883   0.01972  -0.0708   0.3977   1.0000
   8.000   1.2972   0.02937   0.02031  -0.0698   0.3892   1.0000
   8.250   1.3192   0.02968   0.02062  -0.0688   0.3799   1.0000
   8.500   1.3390   0.03021   0.02119  -0.0675   0.3702   1.0000
   8.750   1.3634   0.03038   0.02129  -0.0668   0.3605   1.0000
   9.000   1.3777   0.03108   0.02212  -0.0649   0.3495   1.0000
   9.250   1.4072   0.03111   0.02192  -0.0648   0.3401   1.0000
   9.500   1.4162   0.03187   0.02289  -0.0622   0.3284   1.0000
   9.750   1.4342   0.03241   0.02342  -0.0608   0.3185   1.0000
  10.000   1.4545   0.03269   0.02362  -0.0596   0.3089   1.0000
  10.250   1.4640   0.03357   0.02463  -0.0573   0.2993   1.0000
  10.500   1.4878   0.03372   0.02462  -0.0566   0.2912   1.0000
  10.750   1.4924   0.03490   0.02601  -0.0538   0.2831   1.0000
  11.000   1.5123   0.03532   0.02635  -0.0527   0.2761   1.0000
  11.250   1.5206   0.03643   0.02758  -0.0505   0.2697   1.0000
  11.500   1.5284   0.03731   0.02853  -0.0481   0.2632   1.0000
  11.750   1.5493   0.03772   0.02882  -0.0473   0.2572   1.0000
  12.000   1.5415   0.03933   0.03068  -0.0434   0.2517   1.0000
  12.250   1.5541   0.04007   0.03140  -0.0418   0.2461   1.0000
  12.500   1.5672   0.04103   0.03236  -0.0405   0.2412   1.0000
  12.750   1.5591   0.04309   0.03466  -0.0375   0.2366   1.0000
  13.000   1.5687   0.04419   0.03579  -0.0360   0.2317   1.0000
  13.250   1.5881   0.04491   0.03642  -0.0353   0.2268   1.0000
  13.500   1.5713   0.04779   0.03959  -0.0326   0.2229   1.0000
  13.750   1.5717   0.04966   0.04156  -0.0312   0.2183   1.0000
  14.000   1.6017   0.04961   0.04132  -0.0308   0.2126   1.0000
  14.250   1.5757   0.05358   0.04563  -0.0288   0.2093   1.0000
  14.500   1.5645   0.05670   0.04892  -0.0277   0.2049   1.0000
  14.750   1.6058   0.05555   0.04747  -0.0272   0.1983   1.0000
  15.000   1.5701   0.06093   0.05322  -0.0262   0.1953   1.0000
  15.250   1.5443   0.06597   0.05850  -0.0260   0.1915   1.0000
  15.500   1.5987   0.06325   0.05544  -0.0247   0.1838   1.0000
  15.750   1.5505   0.07059   0.06317  -0.0250   0.1813   1.0000
  16.000   1.4954   0.07983   0.07275  -0.0269   0.1786   1.0000
  16.250   1.5781   0.07328   0.06575  -0.0236   0.1698   1.0000
  16.500   1.5080   0.08411   0.07702  -0.0261   0.1682   1.0000
  17.250   1.4533   0.10109   0.09432  -0.0301   0.1567   1.0000
  17.500   0.9754   0.21728   0.21089  -0.0997   0.1898   1.0000
  17.750   0.9880   0.22003   0.21367  -0.1002   0.1874   1.0000
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