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GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 527 AIRFOIL (goe527-il)
Reynolds number: 100,000
Max Cl/Cd: 46.95 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe527-il-100000-n5.txt
Download as CSV file: xf-goe527-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 527 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1027   0.09653   0.09133  -0.0840   0.9280   0.0571
 -10.250  -0.0908   0.09178   0.08653  -0.0890   0.9189   0.0578
 -10.000  -0.0801   0.08680   0.08151  -0.0941   0.9088   0.0578
  -9.750  -0.0725   0.08169   0.07635  -0.0990   0.8973   0.0575
  -9.500  -0.0667   0.07606   0.07066  -0.1046   0.8862   0.0573
  -9.250  -0.0697   0.07042   0.06497  -0.1093   0.8718   0.0573
  -9.000  -0.0843   0.06346   0.05798  -0.1151   0.8565   0.0579
  -8.750  -0.1482   0.05130   0.04554  -0.1233   0.8376   0.0573
  -8.500  -0.1751   0.04551   0.03934  -0.1238   0.8247   0.0577
  -8.250  -0.1856   0.04123   0.03459  -0.1229   0.8138   0.0584
  -8.000  -0.1885   0.03776   0.03064  -0.1213   0.8032   0.0591
  -7.750  -0.1832   0.03452   0.02680  -0.1199   0.7945   0.0600
  -7.500  -0.1695   0.03281   0.02482  -0.1185   0.7851   0.0608
  -7.250  -0.1480   0.03189   0.02377  -0.1179   0.7768   0.0619
  -7.000  -0.1284   0.03091   0.02263  -0.1169   0.7683   0.0634
  -6.750  -0.1093   0.02965   0.02107  -0.1159   0.7600   0.0653
  -6.500  -0.0891   0.02806   0.01901  -0.1149   0.7530   0.0673
  -6.250  -0.0680   0.02730   0.01820  -0.1139   0.7442   0.0686
  -6.000  -0.0427   0.02652   0.01727  -0.1135   0.7375   0.0703
  -5.750  -0.0214   0.02579   0.01638  -0.1124   0.7290   0.0726
  -5.500   0.0026   0.02492   0.01522  -0.1116   0.7217   0.0759
  -5.250   0.0276   0.02447   0.01475  -0.1112   0.7152   0.0785
  -5.000   0.0504   0.02394   0.01412  -0.1102   0.7072   0.0820
  -4.750   0.0764   0.02327   0.01325  -0.1097   0.7010   0.0858
  -4.500   0.0998   0.02289   0.01287  -0.1089   0.6937   0.0897
  -4.250   0.1244   0.02250   0.01227  -0.1082   0.6865   0.0955
  -4.000   0.1507   0.02200   0.01180  -0.1079   0.6811   0.1005
  -3.750   0.1736   0.02174   0.01143  -0.1069   0.6740   0.1070
  -3.500   0.1976   0.02134   0.01108  -0.1062   0.6675   0.1131
  -3.250   0.2249   0.02104   0.01062  -0.1059   0.6624   0.1211
  -3.000   0.2463   0.02075   0.01043  -0.1048   0.6554   0.1281
  -2.500   0.2969   0.02023   0.00985  -0.1037   0.6446   0.1452
  -2.250   0.3197   0.02008   0.00971  -0.1027   0.6386   0.1541
  -2.000   0.3431   0.01991   0.00957  -0.1018   0.6325   0.1648
  -1.750   0.3691   0.01969   0.00936  -0.1013   0.6277   0.1784
  -1.500   0.3938   0.01953   0.00924  -0.1007   0.6228   0.1991
  -1.250   0.4158   0.01938   0.00926  -0.0997   0.6169   0.2327
  -1.000   0.4402   0.01911   0.00920  -0.0991   0.6119   0.2963
  -0.750   0.4666   0.01877   0.00914  -0.0988   0.6078   0.3926
  -0.500   0.4879   0.01863   0.00932  -0.0976   0.6024   0.4895
  -0.250   0.5090   0.01847   0.00946  -0.0961   0.5972   0.5842
   0.000   0.5335   0.01816   0.00954  -0.0949   0.5927   0.7078
   0.250   0.6114   0.01799   0.00962  -0.1036   0.5882   0.9283
   0.500   0.6737   0.01824   0.00979  -0.1107   0.5818   0.9971
   0.750   0.6972   0.01843   0.00985  -0.1100   0.5769   1.0000
   1.000   0.7207   0.01858   0.00983  -0.1092   0.5729   1.0000
   1.250   0.7404   0.01882   0.00998  -0.1077   0.5682   1.0000
   1.500   0.7578   0.01912   0.01023  -0.1059   0.5629   1.0000
   1.750   0.7793   0.01932   0.01033  -0.1047   0.5582   1.0000
   2.000   0.8046   0.01947   0.01032  -0.1042   0.5541   1.0000
   2.250   0.8213   0.01979   0.01062  -0.1022   0.5487   1.0000
   2.500   0.8395   0.02003   0.01081  -0.1005   0.5423   1.0000
   2.750   0.8646   0.02011   0.01074  -0.0998   0.5367   1.0000
   3.000   0.8809   0.02039   0.01100  -0.0978   0.5299   1.0000
   3.250   0.8997   0.02061   0.01117  -0.0961   0.5233   1.0000
   3.500   0.9252   0.02072   0.01116  -0.0956   0.5183   1.0000
   3.750   0.9413   0.02108   0.01152  -0.0936   0.5126   1.0000
   4.000   0.9589   0.02139   0.01183  -0.0919   0.5068   1.0000
   4.250   0.9824   0.02158   0.01194  -0.0911   0.5019   1.0000
   4.500   1.0037   0.02185   0.01216  -0.0900   0.4971   1.0000
   4.750   1.0168   0.02227   0.01264  -0.0876   0.4908   1.0000
   5.000   1.0375   0.02252   0.01285  -0.0864   0.4854   1.0000
   5.250   1.0637   0.02267   0.01290  -0.0861   0.4811   1.0000
   5.500   1.0717   0.02323   0.01357  -0.0830   0.4746   1.0000
   5.750   1.0889   0.02356   0.01390  -0.0813   0.4690   1.0000
   6.000   1.1137   0.02372   0.01399  -0.0807   0.4644   1.0000
   6.250   1.1206   0.02428   0.01463  -0.0775   0.4579   1.0000
   6.500   1.1327   0.02466   0.01503  -0.0750   0.4516   1.0000
   6.750   1.1566   0.02479   0.01509  -0.0743   0.4465   1.0000
   7.000   1.1562   0.02552   0.01591  -0.0701   0.4394   1.0000
   7.250   1.1690   0.02594   0.01635  -0.0679   0.4331   1.0000
   7.500   1.1870   0.02624   0.01661  -0.0665   0.4276   1.0000
   7.750   1.1882   0.02712   0.01759  -0.0630   0.4202   1.0000
   8.000   1.2043   0.02750   0.01796  -0.0615   0.4143   1.0000
   8.250   1.2113   0.02829   0.01880  -0.0590   0.4075   1.0000
   8.500   1.2183   0.02910   0.01965  -0.0566   0.4003   1.0000
   8.750   1.2350   0.02951   0.02002  -0.0553   0.3941   1.0000
   9.000   1.2333   0.03083   0.02143  -0.0523   0.3857   1.0000
   9.250   1.2517   0.03116   0.02170  -0.0513   0.3793   1.0000
   9.500   1.2472   0.03280   0.02346  -0.0485   0.3706   1.0000
   9.750   1.2622   0.03337   0.02397  -0.0472   0.3639   1.0000
  10.000   1.2612   0.03503   0.02571  -0.0450   0.3559   1.0000
  10.250   1.2721   0.03593   0.02659  -0.0437   0.3490   1.0000
  10.500   1.2762   0.03740   0.02812  -0.0421   0.3419   1.0000
  10.750   1.2812   0.03882   0.02956  -0.0407   0.3347   1.0000
  11.000   1.2915   0.03990   0.03062  -0.0395   0.3283   1.0000
  11.250   1.2899   0.04196   0.03276  -0.0380   0.3207   1.0000
  11.500   1.3076   0.04244   0.03316  -0.0372   0.3149   1.0000
  11.750   1.3000   0.04519   0.03605  -0.0358   0.3077   1.0000
  12.000   1.3088   0.04653   0.03739  -0.0349   0.3020   1.0000
  12.250   1.3190   0.04779   0.03865  -0.0341   0.2969   1.0000
  12.500   1.3160   0.05038   0.04136  -0.0332   0.2910   1.0000
  12.750   1.3257   0.05174   0.04274  -0.0325   0.2862   1.0000
  13.000   1.3416   0.05252   0.04350  -0.0319   0.2821   1.0000
  13.250   1.3331   0.05585   0.04699  -0.0312   0.2766   1.0000
  13.500   1.3374   0.05788   0.04909  -0.0306   0.2719   1.0000
  13.750   1.3561   0.05837   0.04955  -0.0301   0.2681   1.0000
  14.000   1.3526   0.06134   0.05265  -0.0297   0.2634   1.0000
  14.250   1.3457   0.06477   0.05622  -0.0295   0.2583   1.0000
  14.500   1.3545   0.06640   0.05788  -0.0291   0.2541   1.0000
  14.750   1.3800   0.06607   0.05750  -0.0286   0.2508   1.0000
  15.000   1.3535   0.07203   0.06370  -0.0289   0.2454   1.0000
  15.250   1.3468   0.07569   0.06749  -0.0290   0.2404   1.0000
  15.500   1.3620   0.07656   0.06837  -0.0287   0.2367   1.0000
  15.750   1.3751   0.07770   0.06953  -0.0284   0.2330   1.0000
  16.000   1.3299   0.08674   0.07884  -0.0300   0.2262   1.0000
  16.250   1.3370   0.08870   0.08086  -0.0301   0.2219   1.0000
  16.500   1.3650   0.08775   0.07987  -0.0294   0.2190   1.0000
  16.750   1.2859   0.10244   0.09489  -0.0333   0.2099   1.0000
  17.000   1.2943   0.10431   0.09681  -0.0335   0.2062   1.0000
  17.250   1.3227   0.10310   0.09561  -0.0327   0.2040   1.0000
  17.750   1.1286   0.14362   0.13648  -0.0481   0.1773   1.0000
  18.000   1.1414   0.14480   0.13772  -0.0484   0.1757   1.0000
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