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GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 364 AIRFOIL (goe364-il)
Reynolds number: 100,000
Max Cl/Cd: 52.46 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe364-il-100000.txt
Download as CSV file: xf-goe364-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 364 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2482   0.10883   0.10457  -0.0260   1.0000   0.0603
  -8.250  -0.2682   0.10906   0.10493  -0.0221   1.0000   0.0608
  -8.000  -0.2877   0.10920   0.10518  -0.0187   1.0000   0.0613
  -7.750  -0.2771   0.10764   0.10363  -0.0289   0.9895   0.0635
  -7.500  -0.2581   0.10293   0.09892  -0.0367   0.9799   0.0648
  -7.250  -0.2237   0.09713   0.09310  -0.0375   0.9756   0.0674
  -7.000  -0.2002   0.09328   0.08922  -0.0430   0.9665   0.0705
  -6.750  -0.1734   0.08981   0.08570  -0.0548   0.9535   0.0747
  -6.500  -0.1465   0.08554   0.08135  -0.0675   0.9421   0.0765
  -6.250  -0.1311   0.08124   0.07711  -0.0639   0.9350   0.0784
  -6.000  -0.1035   0.07747   0.07332  -0.0675   0.9281   0.0830
  -5.750  -0.0679   0.07575   0.07126  -0.0846   0.9134   0.0895
  -5.500  -0.0472   0.06968   0.06537  -0.0817   0.9109   0.0920
  -5.250  -0.0296   0.06688   0.06256  -0.0822   0.9008   0.0959
  -5.000   0.0196   0.06284   0.05819  -0.0953   0.8947   0.1050
  -4.750   0.0317   0.05966   0.05511  -0.0931   0.8847   0.1075
  -4.500   0.0785   0.05669   0.05175  -0.1021   0.8790   0.1201
  -4.250   0.0895   0.05346   0.04869  -0.0996   0.8688   0.1234
  -4.000   0.1347   0.03396   0.02942  -0.0982   0.8388   0.1397
  -3.750   0.1457   0.04801   0.04302  -0.1037   0.8528   0.1428
  -3.500   0.1827   0.04493   0.03975  -0.1073   0.8473   0.1570
  -3.250   0.2033   0.04311   0.03779  -0.1075   0.8359   0.1713
  -3.000   0.2373   0.04044   0.03502  -0.1093   0.8304   0.1908
  -2.750   0.2545   0.03905   0.03356  -0.1082   0.8185   0.2118
  -2.500   0.2794   0.03704   0.03148  -0.1082   0.8102   0.2408
  -2.250   0.3009   0.03533   0.02973  -0.1074   0.8003   0.2749
  -1.750   0.3413   0.03204   0.02641  -0.1043   0.7816   0.3704
  -1.500   0.3553   0.03062   0.02506  -0.1014   0.7697   0.4080
  -1.250   0.4461   0.02900   0.02132  -0.1108   0.7628   0.1673
  -1.000   0.4730   0.02683   0.01882  -0.1095   0.7513   0.1280
  -0.750   0.5021   0.02574   0.01731  -0.1085   0.7411   0.1139
  -0.500   0.5342   0.02463   0.01576  -0.1080   0.7320   0.1065
  -0.250   0.5581   0.02414   0.01510  -0.1067   0.7202   0.1062
   0.000   0.5888   0.02337   0.01417  -0.1065   0.7119   0.1075
   0.250   0.6137   0.02292   0.01363  -0.1054   0.7008   0.1071
   0.500   0.6391   0.02253   0.01319  -0.1045   0.6905   0.1081
   0.750   0.6688   0.02197   0.01256  -0.1041   0.6819   0.1106
   1.000   0.6912   0.02180   0.01239  -0.1027   0.6703   0.1151
   1.250   0.7190   0.02135   0.01189  -0.1020   0.6603   0.1241
   1.500   0.7474   0.02095   0.01138  -0.1013   0.6494   0.1373
   1.750   0.7716   0.02062   0.01121  -0.1003   0.6377   0.1868
   2.000   0.8305   0.01893   0.01079  -0.1060   0.6276   1.0000
   2.250   0.8549   0.01916   0.01085  -0.1050   0.6181   1.0000
   2.500   0.8782   0.01946   0.01103  -0.1040   0.6089   1.0000
   2.750   0.9048   0.01961   0.01100  -0.1034   0.6005   1.0000
   3.000   0.9264   0.01997   0.01132  -0.1022   0.5907   1.0000
   3.250   0.9547   0.02007   0.01124  -0.1018   0.5830   1.0000
   3.500   0.9747   0.02049   0.01166  -0.1004   0.5730   1.0000
   3.750   1.0040   0.02057   0.01158  -0.1003   0.5657   1.0000
   4.000   1.0232   0.02098   0.01202  -0.0987   0.5552   1.0000
   4.250   1.0483   0.02120   0.01215  -0.0980   0.5464   1.0000
   4.500   1.0725   0.02141   0.01230  -0.0971   0.5367   1.0000
   4.750   1.0941   0.02176   0.01265  -0.0959   0.5266   1.0000
   5.000   1.1231   0.02186   0.01259  -0.0958   0.5182   1.0000
   5.250   1.1416   0.02229   0.01309  -0.0941   0.5069   1.0000
   5.500   1.1647   0.02259   0.01337  -0.0931   0.4964   1.0000
   5.750   1.1929   0.02274   0.01335  -0.0929   0.4865   1.0000
   6.000   1.2110   0.02319   0.01387  -0.0912   0.4742   1.0000
   6.250   1.2323   0.02365   0.01431  -0.0900   0.4628   1.0000
   6.500   1.2578   0.02400   0.01457  -0.0894   0.4520   1.0000
   6.750   1.2795   0.02445   0.01499  -0.0883   0.4401   1.0000
   7.000   1.2974   0.02506   0.01566  -0.0867   0.4282   1.0000
   7.250   1.3198   0.02562   0.01619  -0.0858   0.4175   1.0000
   7.500   1.3436   0.02611   0.01660  -0.0851   0.4072   1.0000
   7.750   1.3587   0.02685   0.01745  -0.0832   0.3964   1.0000
   8.000   1.3827   0.02738   0.01791  -0.0826   0.3872   1.0000
   8.250   1.3991   0.02800   0.01863  -0.0809   0.3774   1.0000
   8.500   1.4173   0.02866   0.01934  -0.0795   0.3685   1.0000
   8.750   1.4388   0.02911   0.01976  -0.0785   0.3598   1.0000
   9.000   1.4522   0.02987   0.02066  -0.0764   0.3512   1.0000
   9.250   1.4763   0.03025   0.02098  -0.0759   0.3433   1.0000
   9.500   1.4860   0.03114   0.02207  -0.0733   0.3353   1.0000
   9.750   1.5102   0.03155   0.02240  -0.0729   0.3280   1.0000
  10.000   1.5185   0.03253   0.02360  -0.0702   0.3206   1.0000
  10.250   1.5405   0.03301   0.02405  -0.0694   0.3134   1.0000
  10.500   1.5493   0.03401   0.02523  -0.0670   0.3064   1.0000
  10.750   1.5676   0.03460   0.02583  -0.0657   0.2991   1.0000
  11.000   1.5779   0.03561   0.02695  -0.0635   0.2923   1.0000
  11.250   1.5907   0.03645   0.02790  -0.0616   0.2853   1.0000
  11.500   1.6069   0.03744   0.02892  -0.0604   0.2787   1.0000
  11.750   1.6079   0.03858   0.03024  -0.0569   0.2722   1.0000
  12.000   1.6334   0.03940   0.03100  -0.0570   0.2648   1.0000
  12.250   1.6227   0.04093   0.03278  -0.0522   0.2592   1.0000
  12.500   1.6576   0.04153   0.03324  -0.0535   0.2508   1.0000
  12.750   1.6373   0.04344   0.03546  -0.0479   0.2462   1.0000
  13.000   1.6570   0.04412   0.03609  -0.0472   0.2385   1.0000
  13.250   1.6503   0.04596   0.03810  -0.0439   0.2330   1.0000
  13.500   1.6386   0.04790   0.04025  -0.0405   0.2277   1.0000
  13.750   1.6610   0.04837   0.04061  -0.0401   0.2197   1.0000
  14.000   1.6369   0.05126   0.04380  -0.0364   0.2159   1.0000
  14.250   1.6439   0.05236   0.04492  -0.0350   0.2095   1.0000
  14.500   1.6463   0.05416   0.04679  -0.0336   0.2042   1.0000
  14.750   1.6194   0.05804   0.05097  -0.0312   0.2010   1.0000
  15.000   1.6092   0.06084   0.05393  -0.0299   0.1966   1.0000
  15.250   1.6345   0.06081   0.05382  -0.0295   0.1903   1.0000
  15.500   1.5988   0.06630   0.05963  -0.0283   0.1883   1.0000
  15.750   1.5583   0.07302   0.06664  -0.0282   0.1864   1.0000
  16.000   1.4446   0.09125   0.08526  -0.0326   0.1890   1.0000
  16.250   1.5804   0.07503   0.06871  -0.0273   0.1761   1.0000
  16.500   1.5213   0.08517   0.07917  -0.0292   0.1755   1.0000
  17.250   1.5031   0.09573   0.09004  -0.0314   0.1636   1.0000
  17.500   1.0121   0.21238   0.20616  -0.0972   0.2149   1.0000
  17.750   1.0225   0.21499   0.20883  -0.0981   0.2108   1.0000
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