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GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 365 AIRFOIL (goe365-il)
Reynolds number: 500,000
Max Cl/Cd: 107.16 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe365-il-500000.txt
Download as CSV file: xf-goe365-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 365 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2042   0.09275   0.09056  -0.0587   0.9852   0.0227
  -9.000  -0.1960   0.08663   0.08446  -0.0684   0.9741   0.0229
  -8.750  -0.1847   0.08123   0.07905  -0.0744   0.9623   0.0230
  -8.500  -0.1663   0.07760   0.07541  -0.0763   0.9549   0.0233
  -8.250  -0.1411   0.07429   0.07209  -0.0800   0.9469   0.0236
  -8.000  -0.1107   0.06991   0.06767  -0.0881   0.9374   0.0242
  -7.750  -0.0789   0.06471   0.06239  -0.0991   0.9221   0.0251
  -7.500  -0.0553   0.05910   0.05661  -0.1097   0.8986   0.0266
  -7.250  -0.0563   0.05147   0.04852  -0.1177   0.8680   0.0275
  -7.000  -0.0528   0.04764   0.04462  -0.1173   0.8540   0.0278
  -6.750  -0.0420   0.04562   0.04252  -0.1167   0.8427   0.0281
  -6.500  -0.0293   0.04381   0.04062  -0.1162   0.8332   0.0284
  -6.250  -0.0165   0.04179   0.03851  -0.1157   0.8238   0.0290
  -6.000  -0.0026   0.03959   0.03617  -0.1153   0.8155   0.0298
  -5.750   0.0131   0.03635   0.03232  -0.1139   0.8070   0.0329
  -5.500   0.0220   0.03215   0.02798  -0.1129   0.7996   0.0336
  -5.250   0.0399   0.03054   0.02631  -0.1123   0.7924   0.0341
  -5.000   0.0591   0.02915   0.02483  -0.1116   0.7864   0.0348
  -4.750   0.0787   0.02769   0.02325  -0.1108   0.7806   0.0360
  -4.500   0.1038   0.02755   0.02256  -0.1089   0.7754   0.0396
  -4.250   0.1183   0.02364   0.01849  -0.1080   0.7708   0.0409
  -4.000   0.1401   0.02248   0.01732  -0.1074   0.7656   0.0420
  -3.750   0.1633   0.02153   0.01627  -0.1068   0.7610   0.0439
  -3.500   0.1921   0.02265   0.01700  -0.1057   0.7564   0.0480
  -3.250   0.2094   0.01911   0.01337  -0.1048   0.7518   0.0503
  -3.000   0.2336   0.01826   0.01247  -0.1043   0.7471   0.0522
  -2.750   0.2598   0.01790   0.01194  -0.1037   0.7427   0.0563
  -2.500   0.2832   0.01669   0.01058  -0.1030   0.7383   0.0617
  -2.250   0.3083   0.01608   0.00995  -0.1025   0.7332   0.0657
  -2.000   0.3333   0.01541   0.00911  -0.1019   0.7286   0.0743
  -1.750   0.3595   0.01479   0.00847  -0.1016   0.7239   0.0788
  -1.500   0.3897   0.01287   0.00613  -0.0999   0.7188   0.0458
  -1.250   0.4157   0.01228   0.00546  -0.0993   0.7126   0.0455
  -1.000   0.4414   0.01172   0.00485  -0.0986   0.7061   0.0447
  -0.750   0.4660   0.01126   0.00436  -0.0977   0.6986   0.0442
  -0.500   0.4912   0.01093   0.00397  -0.0970   0.6917   0.0444
  -0.250   0.5151   0.01061   0.00366  -0.0960   0.6830   0.0447
   0.000   0.5396   0.01038   0.00338  -0.0951   0.6747   0.0453
   0.250   0.5639   0.01017   0.00318  -0.0942   0.6659   0.0465
   0.500   0.5890   0.01003   0.00301  -0.0935   0.6582   0.0475
   0.750   0.6136   0.00987   0.00283  -0.0927   0.6492   0.0483
   1.000   0.6380   0.00967   0.00262  -0.0919   0.6401   0.0501
   1.250   0.6626   0.00958   0.00249  -0.0911   0.6305   0.0530
   1.500   0.6874   0.00952   0.00241  -0.0903   0.6189   0.0570
   1.750   0.7926   0.00754   0.00268  -0.1077   0.5995   1.0000
   2.000   0.8129   0.00763   0.00267  -0.1061   0.5818   1.0000
   2.250   0.8326   0.00777   0.00269  -0.1043   0.5625   1.0000
   2.500   0.8511   0.00796   0.00274  -0.1024   0.5411   1.0000
   2.750   0.8694   0.00818   0.00283  -0.1004   0.5185   1.0000
   3.000   0.8878   0.00842   0.00294  -0.0985   0.4976   1.0000
   3.250   0.9064   0.00867   0.00306  -0.0966   0.4789   1.0000
   3.500   0.9256   0.00890   0.00320  -0.0949   0.4625   1.0000
   4.250   0.9832   0.00963   0.00368  -0.0898   0.4150   1.0000
   4.500   1.0023   0.00988   0.00385  -0.0881   0.3991   1.0000
   4.750   1.0212   0.01014   0.00405  -0.0864   0.3826   1.0000
   5.000   1.0398   0.01041   0.00424  -0.0847   0.3660   1.0000
   5.250   1.0580   0.01070   0.00446  -0.0828   0.3485   1.0000
   5.500   1.0754   0.01101   0.00469  -0.0809   0.3301   1.0000
   5.750   1.0919   0.01137   0.00495  -0.0788   0.3109   1.0000
   6.000   1.1074   0.01176   0.00523  -0.0766   0.2925   1.0000
   6.250   1.1233   0.01213   0.00552  -0.0744   0.2757   1.0000
   6.500   1.1374   0.01252   0.00584  -0.0719   0.2615   1.0000
   6.750   1.1513   0.01289   0.00615  -0.0694   0.2494   1.0000
   7.000   1.1664   0.01323   0.00647  -0.0671   0.2401   1.0000
   7.250   1.1804   0.01364   0.00683  -0.0647   0.2319   1.0000
   7.500   1.1971   0.01397   0.00717  -0.0629   0.2252   1.0000
   7.750   1.2117   0.01440   0.00757  -0.0607   0.2194   1.0000
   8.000   1.2286   0.01475   0.00794  -0.0590   0.2148   1.0000
   8.250   1.2455   0.01512   0.00833  -0.0573   0.2105   1.0000
   8.500   1.2602   0.01559   0.00879  -0.0553   0.2056   1.0000
   8.750   1.2767   0.01600   0.00922  -0.0537   0.2007   1.0000
   9.000   1.2936   0.01640   0.00964  -0.0522   0.1956   1.0000
   9.250   1.3076   0.01695   0.01017  -0.0503   0.1906   1.0000
   9.500   1.3240   0.01740   0.01068  -0.0488   0.1868   1.0000
   9.750   1.3412   0.01783   0.01115  -0.0475   0.1824   1.0000
  10.000   1.3556   0.01841   0.01173  -0.0459   0.1776   1.0000
  10.250   1.3701   0.01901   0.01235  -0.0444   0.1731   1.0000
  10.500   1.3872   0.01948   0.01289  -0.0432   0.1681   1.0000
  10.750   1.4005   0.02018   0.01359  -0.0417   0.1626   1.0000
  11.000   1.4159   0.02078   0.01424  -0.0404   0.1573   1.0000
  11.250   1.4306   0.02145   0.01493  -0.0392   0.1509   1.0000
  11.500   1.4437   0.02223   0.01574  -0.0378   0.1441   1.0000
  11.750   1.4561   0.02309   0.01659  -0.0365   0.1343   1.0000
  12.000   1.4656   0.02418   0.01761  -0.0350   0.1151   1.0000
  12.250   1.4650   0.02602   0.01927  -0.0328   0.0930   1.0000
  12.500   1.4668   0.02778   0.02099  -0.0309   0.0822   1.0000
  12.750   1.4680   0.02964   0.02284  -0.0291   0.0701   1.0000
  13.000   1.4553   0.03272   0.02568  -0.0266   0.0366   1.0000
  13.250   1.4471   0.03558   0.02853  -0.0247   0.0275   1.0000
  13.500   1.4461   0.03793   0.03096  -0.0234   0.0247   1.0000
  13.750   1.4451   0.04035   0.03346  -0.0222   0.0228   1.0000
  14.000   1.4472   0.04254   0.03577  -0.0214   0.0216   1.0000
  14.250   1.4469   0.04504   0.03838  -0.0206   0.0206   1.0000
  14.500   1.4437   0.04793   0.04136  -0.0200   0.0198   1.0000
  14.750   1.4377   0.05124   0.04478  -0.0195   0.0191   1.0000
  15.000   1.4283   0.05511   0.04878  -0.0193   0.0185   1.0000
  15.250   1.4267   0.05820   0.05199  -0.0192   0.0180   1.0000
  15.500   1.4227   0.06165   0.05556  -0.0194   0.0176   1.0000
  15.750   1.4157   0.06564   0.05967  -0.0198   0.0171   1.0000
  16.000   1.4077   0.06987   0.06401  -0.0205   0.0168   1.0000
  16.250   1.3978   0.07450   0.06876  -0.0214   0.0165   1.0000
  16.500   1.3865   0.07942   0.07380  -0.0225   0.0162   1.0000
  16.750   1.3756   0.08442   0.07892  -0.0237   0.0161   1.0000
  17.000   1.3608   0.09010   0.08472  -0.0253   0.0158   1.0000
  17.250   1.3484   0.09549   0.09023  -0.0269   0.0158   1.0000
  17.500   1.3337   0.10134   0.09618  -0.0288   0.0155   1.0000
  17.750   1.3167   0.10768   0.10263  -0.0310   0.0153   1.0000
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