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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 200,000
Max Cl/Cd: 81.91 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe529-il-200000-n5.txt
Download as CSV file: xf-goe529-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2432   0.11241   0.10894  -0.0376   1.0000   0.0240
  -9.750  -0.2409   0.11008   0.10665  -0.0382   1.0000   0.0263
  -9.500  -0.2422   0.10789   0.10453  -0.0390   1.0000   0.0271
  -9.000  -0.2305   0.09867   0.09535  -0.0434   0.9890   0.0207
  -8.750  -0.2163   0.09455   0.09124  -0.0472   0.9795   0.0206
  -8.500  -0.2007   0.09049   0.08717  -0.0514   0.9692   0.0204
  -8.250  -0.1872   0.08526   0.08193  -0.0582   0.9560   0.0209
  -8.000  -0.1628   0.08314   0.07980  -0.0608   0.9453   0.0231
  -7.750  -0.1424   0.07922   0.07585  -0.0663   0.9297   0.0243
  -7.500  -0.1247   0.07473   0.07131  -0.0723   0.9101   0.0242
  -7.250  -0.1083   0.07038   0.06689  -0.0782   0.8898   0.0242
  -7.000  -0.0938   0.06628   0.06271  -0.0834   0.8693   0.0246
  -6.750  -0.0801   0.06232   0.05866  -0.0881   0.8499   0.0256
  -6.500  -0.0669   0.05717   0.05336  -0.0942   0.8318   0.0268
  -6.250  -0.0519   0.05204   0.04806  -0.0990   0.8158   0.0272
  -6.000  -0.0347   0.04552   0.04131  -0.1046   0.8014   0.0280
  -5.750  -0.0171   0.04430   0.03999  -0.1049   0.7877   0.0292
  -5.500   0.0032   0.04289   0.03845  -0.1055   0.7738   0.0307
  -5.250   0.0245   0.03916   0.03448  -0.1078   0.7601   0.0320
  -5.000   0.0466   0.03428   0.02924  -0.1101   0.7475   0.0328
  -4.750   0.0688   0.02796   0.02229  -0.1119   0.7365   0.0353
  -4.500   0.0906   0.02350   0.01709  -0.1123   0.7258   0.0362
  -4.250   0.1138   0.02100   0.01404  -0.1121   0.7160   0.0373
  -4.000   0.1384   0.01992   0.01274  -0.1119   0.7073   0.0387
  -3.750   0.1638   0.01883   0.01137  -0.1116   0.6988   0.0396
  -3.500   0.1897   0.01780   0.01004  -0.1113   0.6917   0.0404
  -3.250   0.2159   0.01693   0.00890  -0.1109   0.6842   0.0412
  -3.000   0.2423   0.01622   0.00795  -0.1106   0.6778   0.0422
  -2.750   0.2690   0.01567   0.00722  -0.1103   0.6710   0.0436
  -2.500   0.2956   0.01521   0.00657  -0.1099   0.6651   0.0452
  -2.250   0.3223   0.01473   0.00595  -0.1096   0.6591   0.0461
  -2.000   0.3490   0.01432   0.00542  -0.1093   0.6531   0.0470
  -1.750   0.3754   0.01392   0.00493  -0.1089   0.6478   0.0481
  -1.500   0.4018   0.01360   0.00460  -0.1086   0.6418   0.0500
  -1.250   0.4284   0.01341   0.00436  -0.1083   0.6365   0.0524
  -1.000   0.4552   0.01325   0.00414  -0.1080   0.6313   0.0554
  -0.750   0.4818   0.01309   0.00396  -0.1076   0.6253   0.0602
  -0.500   0.5084   0.01300   0.00385  -0.1073   0.6200   0.0705
  -0.250   0.5350   0.01288   0.00375  -0.1071   0.6146   0.0863
   0.000   0.5615   0.01278   0.00371  -0.1068   0.6087   0.1052
   0.250   0.5881   0.01276   0.00368  -0.1065   0.6033   0.1257
   0.500   0.6144   0.01270   0.00370  -0.1062   0.5971   0.1516
   1.000   0.6657   0.01238   0.00377  -0.1055   0.5855   0.2934
   1.250   0.7085   0.01096   0.00385  -0.1087   0.5781   1.0000
   1.500   0.7343   0.01109   0.00384  -0.1082   0.5721   1.0000
   1.750   0.7600   0.01119   0.00390  -0.1077   0.5643   1.0000
   2.000   0.7856   0.01132   0.00392  -0.1072   0.5573   1.0000
   2.250   0.8110   0.01142   0.00399  -0.1067   0.5484   1.0000
   2.500   0.8362   0.01154   0.00403  -0.1061   0.5399   1.0000
   2.750   0.8614   0.01165   0.00410  -0.1055   0.5303   1.0000
   3.000   0.8866   0.01178   0.00419  -0.1050   0.5209   1.0000
   3.250   0.9114   0.01192   0.00427  -0.1044   0.5108   1.0000
   3.500   0.9360   0.01206   0.00436  -0.1038   0.4996   1.0000
   3.750   0.9605   0.01222   0.00447  -0.1031   0.4878   1.0000
   4.000   0.9848   0.01240   0.00461  -0.1025   0.4772   1.0000
   4.250   1.0089   0.01260   0.00476  -0.1018   0.4673   1.0000
   4.500   1.0331   0.01281   0.00494  -0.1012   0.4574   1.0000
   4.750   1.0572   0.01304   0.00516  -0.1005   0.4485   1.0000
   5.000   1.0809   0.01330   0.00537  -0.0998   0.4398   1.0000
   5.250   1.1050   0.01354   0.00562  -0.0992   0.4315   1.0000
   5.500   1.1284   0.01382   0.00589  -0.0985   0.4242   1.0000
   5.750   1.1525   0.01407   0.00618  -0.0979   0.4167   1.0000
   6.000   1.1757   0.01437   0.00647  -0.0971   0.4097   1.0000
   6.250   1.1992   0.01464   0.00679  -0.0965   0.4020   1.0000
   6.500   1.2217   0.01497   0.00713  -0.0957   0.3942   1.0000
   6.750   1.2446   0.01525   0.00748  -0.0949   0.3856   1.0000
   7.000   1.2663   0.01559   0.00784  -0.0940   0.3769   1.0000
   7.250   1.2873   0.01594   0.00821  -0.0929   0.3652   1.0000
   7.500   1.3066   0.01632   0.00861  -0.0916   0.3501   1.0000
   7.750   1.3245   0.01674   0.00902  -0.0901   0.3311   1.0000
   8.000   1.3420   0.01720   0.00947  -0.0885   0.3133   1.0000
   8.250   1.3581   0.01771   0.00996  -0.0867   0.2951   1.0000
   8.500   1.3718   0.01832   0.01052  -0.0847   0.2762   1.0000
   8.750   1.3831   0.01900   0.01117  -0.0822   0.2539   1.0000
   9.000   1.3895   0.01984   0.01191  -0.0790   0.2311   1.0000
   9.500   1.3915   0.02229   0.01401  -0.0719   0.1577   1.0000
   9.750   1.3840   0.02420   0.01565  -0.0678   0.1239   1.0000
  10.000   1.3828   0.02589   0.01726  -0.0648   0.1070   1.0000
  10.250   1.3850   0.02746   0.01882  -0.0624   0.0788   1.0000
  10.500   1.3710   0.03037   0.02145  -0.0592   0.0472   1.0000
  11.000   1.3622   0.03531   0.02637  -0.0553   0.0218   1.0000
  11.250   1.3621   0.03764   0.02877  -0.0540   0.0195   1.0000
  11.500   1.3634   0.03994   0.03117  -0.0529   0.0181   1.0000
  11.750   1.3645   0.04235   0.03373  -0.0520   0.0170   1.0000
  12.000   1.3645   0.04496   0.03648  -0.0513   0.0160   1.0000
  12.250   1.3629   0.04783   0.03949  -0.0507   0.0152   1.0000
  12.500   1.3609   0.05084   0.04263  -0.0503   0.0147   1.0000
  12.750   1.3565   0.05422   0.04615  -0.0500   0.0142   1.0000
  13.000   1.3496   0.05802   0.05010  -0.0499   0.0137   1.0000
  13.250   1.3421   0.06203   0.05426  -0.0501   0.0134   1.0000
  13.500   1.3369   0.06589   0.05825  -0.0504   0.0132   1.0000
  13.750   1.3332   0.06966   0.06215  -0.0508   0.0130   1.0000
  14.000   1.3290   0.07359   0.06624  -0.0513   0.0127   1.0000
  14.250   1.3247   0.07763   0.07041  -0.0520   0.0124   1.0000
  14.500   1.3213   0.08164   0.07455  -0.0527   0.0120   1.0000
  14.750   1.3175   0.08578   0.07881  -0.0536   0.0117   1.0000
  15.000   1.3141   0.08990   0.08304  -0.0546   0.0114   1.0000
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