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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 500,000
Max Cl/Cd: 105.31 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe417-il-500000.txt
Download as CSV file: xf-goe417-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2962   0.10326   0.10112  -0.0216   1.0000   0.0130
  -8.250  -0.3003   0.10161   0.09951  -0.0195   1.0000   0.0131
  -8.000  -0.3043   0.10007   0.09801  -0.0178   0.9999   0.0132
  -7.750  -0.2856   0.09647   0.09441  -0.0220   0.9976   0.0134
  -7.500  -0.2655   0.09286   0.09079  -0.0268   0.9949   0.0142
  -7.250  -0.2472   0.08931   0.08725  -0.0313   0.9908   0.0152
  -7.000  -0.2248   0.08556   0.08349  -0.0373   0.9865   0.0158
  -6.750  -0.1853   0.08127   0.07917  -0.0514   0.9821   0.0162
  -6.500  -0.1557   0.07720   0.07507  -0.0604   0.9762   0.0163
  -6.250  -0.1332   0.07215   0.07002  -0.0641   0.9737   0.0164
  -6.000  -0.1109   0.06826   0.06612  -0.0666   0.9720   0.0166
  -5.750  -0.0792   0.06442   0.06226  -0.0724   0.9704   0.0171
  -5.500  -0.0521   0.06109   0.05890  -0.0773   0.9647   0.0177
  -5.250  -0.0157   0.05717   0.05493  -0.0845   0.9610   0.0189
  -5.000   0.0448   0.05255   0.05016  -0.0984   0.9574   0.0205
  -4.750   0.0810   0.04883   0.04633  -0.1041   0.9506   0.0206
  -4.500   0.1018   0.04428   0.04175  -0.1065   0.9441   0.0210
  -4.250   0.1237   0.04183   0.03926  -0.1076   0.9364   0.0215
  -4.000   0.1495   0.03938   0.03674  -0.1094   0.9286   0.0222
  -3.750   0.1764   0.03691   0.03417  -0.1113   0.9204   0.0235
  -3.500   0.2208   0.03404   0.03103  -0.1152   0.9137   0.0261
  -3.250   0.2520   0.03122   0.02799  -0.1165   0.9055   0.0263
  -3.000   0.2721   0.02737   0.02406  -0.1176   0.8981   0.0272
  -2.750   0.2950   0.02584   0.02247  -0.1177   0.8884   0.0281
  -2.500   0.3221   0.02409   0.02057  -0.1181   0.8800   0.0297
  -2.250   0.3562   0.02272   0.01885  -0.1180   0.8710   0.0335
  -2.000   0.3821   0.01912   0.01494  -0.1185   0.8614   0.0350
  -1.750   0.4071   0.01793   0.01367  -0.1184   0.8515   0.0362
  -1.500   0.4332   0.01690   0.01249  -0.1182   0.8404   0.0383
  -1.250   0.4615   0.01654   0.01186  -0.1175   0.8277   0.0430
  -1.000   0.4872   0.01446   0.00952  -0.1173   0.8149   0.0464
  -0.750   0.5128   0.01384   0.00881  -0.1170   0.8008   0.0497
  -0.500   0.5407   0.01466   0.00941  -0.1161   0.7849   0.0561
   1.500   0.7414   0.00989   0.00298  -0.1094   0.5801   0.0440
   1.750   0.7657   0.00979   0.00277  -0.1086   0.5526   0.0438
   2.000   0.7894   0.00974   0.00257  -0.1077   0.5201   0.0441
   2.250   0.8129   0.00978   0.00246  -0.1068   0.4848   0.0448
   2.500   0.8367   0.00988   0.00241  -0.1060   0.4530   0.0470
   2.750   0.8610   0.01006   0.00245  -0.1053   0.4271   0.0476
   3.000   0.8856   0.01023   0.00252  -0.1046   0.4060   0.0489
   3.250   0.9104   0.01041   0.00261  -0.1040   0.3891   0.0518
   3.500   0.9354   0.01056   0.00272  -0.1034   0.3755   0.0662
   3.750   0.9650   0.00928   0.00309  -0.1044   0.3636   1.0000
   4.000   0.9899   0.00951   0.00325  -0.1038   0.3535   1.0000
   4.250   1.0148   0.00974   0.00341  -0.1032   0.3441   1.0000
   4.500   1.0400   0.00994   0.00358  -0.1027   0.3357   1.0000
   4.750   1.0644   0.01020   0.00378  -0.1021   0.3275   1.0000
   5.000   1.0898   0.01038   0.00398  -0.1017   0.3197   1.0000
   5.250   1.1142   0.01064   0.00420  -0.1011   0.3120   1.0000
   5.500   1.1394   0.01082   0.00440  -0.1006   0.3040   1.0000
   5.750   1.1639   0.01106   0.00461  -0.1000   0.2934   1.0000
   6.000   1.1880   0.01130   0.00483  -0.0994   0.2776   1.0000
   6.250   1.2120   0.01157   0.00505  -0.0988   0.2614   1.0000
   6.500   1.2358   0.01185   0.00529  -0.0981   0.2464   1.0000
   6.750   1.2585   0.01223   0.00557  -0.0973   0.2241   1.0000
   7.000   1.2804   0.01268   0.00592  -0.0964   0.2000   1.0000
   7.250   1.3020   0.01316   0.00631  -0.0955   0.1799   1.0000
   7.500   1.3231   0.01367   0.00675  -0.0945   0.1624   1.0000
   7.750   1.3434   0.01425   0.00723  -0.0934   0.1448   1.0000
   8.000   1.3629   0.01491   0.00777  -0.0922   0.1211   1.0000
   8.250   1.3719   0.01659   0.00896  -0.0895   0.0463   1.0000
   8.500   1.3851   0.01784   0.01007  -0.0873   0.0223   1.0000
   8.750   1.4032   0.01856   0.01088  -0.0857   0.0192   1.0000
   9.000   1.4196   0.01937   0.01177  -0.0839   0.0172   1.0000
   9.250   1.4323   0.02047   0.01299  -0.0816   0.0156   1.0000
   9.500   1.4434   0.02151   0.01418  -0.0790   0.0148   1.0000
   9.750   1.4543   0.02238   0.01515  -0.0763   0.0143   1.0000
  10.000   1.4624   0.02337   0.01625  -0.0733   0.0138   1.0000
  10.250   1.4686   0.02448   0.01748  -0.0702   0.0133   1.0000
  10.500   1.4735   0.02570   0.01880  -0.0671   0.0129   1.0000
  10.750   1.4773   0.02703   0.02022  -0.0641   0.0123   1.0000
  11.000   1.4786   0.02859   0.02187  -0.0611   0.0118   1.0000
  11.250   1.4764   0.03051   0.02389  -0.0581   0.0114   1.0000
  11.500   1.4681   0.03309   0.02661  -0.0549   0.0110   1.0000
  11.750   1.4576   0.03617   0.02982  -0.0520   0.0108   1.0000
  12.000   1.4557   0.03868   0.03245  -0.0500   0.0106   1.0000
  12.250   1.4574   0.04095   0.03483  -0.0486   0.0105   1.0000
  12.500   1.4602   0.04314   0.03715  -0.0474   0.0103   1.0000
  12.750   1.4610   0.04571   0.03984  -0.0464   0.0102   1.0000
  13.000   1.4615   0.04843   0.04269  -0.0456   0.0100   1.0000
  13.250   1.4614   0.05132   0.04571  -0.0449   0.0098   1.0000
  13.500   1.4608   0.05443   0.04896  -0.0444   0.0097   1.0000
  13.750   1.4597   0.05771   0.05237  -0.0441   0.0096   1.0000
  14.000   1.4580   0.06117   0.05599  -0.0440   0.0095   1.0000
  14.250   1.4554   0.06490   0.05988  -0.0441   0.0094   1.0000
  14.500   1.4515   0.06891   0.06404  -0.0445   0.0092   1.0000
  14.750   1.4466   0.07318   0.06848  -0.0452   0.0091   1.0000
  15.000   1.4411   0.07764   0.07309  -0.0464   0.0090   1.0000
  15.250   1.4339   0.08250   0.07812  -0.0479   0.0089   1.0000
  15.500   1.4260   0.08765   0.08342  -0.0497   0.0088   1.0000
  15.750   1.4171   0.09316   0.08909  -0.0519   0.0087   1.0000
  16.000   1.4083   0.09878   0.09486  -0.0545   0.0086   1.0000
  16.250   1.3975   0.10496   0.10120  -0.0574   0.0086   1.0000
  16.500   1.3878   0.11110   0.10749  -0.0606   0.0085   1.0000
  16.750   1.3757   0.11797   0.11452  -0.0644   0.0085   1.0000
  17.000   1.3587   0.12620   0.12296  -0.0691   0.0086   1.0000
  17.250   1.3427   0.13450   0.13145  -0.0741   0.0087   1.0000
  17.500   1.3241   0.14374   0.14090  -0.0799   0.0089   1.0000
  17.750   1.3077   0.15277   0.15009  -0.0857   0.0090   1.0000
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