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GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 375 AIRFOIL (goe375-il)
Reynolds number: 500,000
Max Cl/Cd: 88.9 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe375-il-500000.txt
Download as CSV file: xf-goe375-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 375 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2846   0.08979   0.08770  -0.0129   1.0000   0.0120
  -8.500  -0.2811   0.08652   0.08445  -0.0135   1.0000   0.0123
  -8.250  -0.2777   0.08335   0.08130  -0.0142   1.0000   0.0124
  -8.000  -0.2748   0.08012   0.07809  -0.0148   1.0000   0.0126
  -7.750  -0.2725   0.07692   0.07492  -0.0154   1.0000   0.0129
  -7.500  -0.2709   0.07386   0.07189  -0.0159   1.0000   0.0132
  -7.250  -0.2705   0.07091   0.06896  -0.0162   1.0000   0.0133
  -7.000  -0.2730   0.06818   0.06627  -0.0162   1.0000   0.0136
  -6.750  -0.2774   0.06576   0.06390  -0.0161   1.0000   0.0138
  -6.500  -0.2761   0.06276   0.06093  -0.0174   1.0000   0.0138
  -6.250  -0.2740   0.05984   0.05804  -0.0195   1.0000   0.0140
  -6.000  -0.2611   0.05599   0.05417  -0.0242   0.9980   0.0140
  -5.750  -0.2300   0.05055   0.04865  -0.0328   0.9923   0.0141
  -5.500  -0.1979   0.04515   0.04313  -0.0400   0.9859   0.0141
  -5.250  -0.2272   0.05833   0.05609  -0.0377   0.9937   0.0141
  -5.000  -0.2054   0.05320   0.05096  -0.0407   0.9880   0.0144
  -4.750  -0.1749   0.04934   0.04706  -0.0450   0.9829   0.0147
  -4.500  -0.1422   0.04583   0.04346  -0.0490   0.9739   0.0154
  -4.250  -0.1040   0.04219   0.03968  -0.0534   0.9645   0.0166
  -4.000  -0.0490   0.03952   0.03661  -0.0579   0.9521   0.0178
  -3.750  -0.0100   0.03635   0.03317  -0.0608   0.9336   0.0178
  -3.500   0.0165   0.03173   0.02847  -0.0633   0.9123   0.0181
  -3.250   0.0407   0.02930   0.02590  -0.0640   0.8898   0.0185
  -3.000   0.0652   0.02734   0.02374  -0.0639   0.8701   0.0191
  -2.750   0.0903   0.02555   0.02171  -0.0633   0.8527   0.0205
  -2.500   0.1228   0.02521   0.02091  -0.0616   0.8376   0.0222
  -2.250   0.1491   0.02420   0.01951  -0.0604   0.8234   0.0224
  -2.000   0.1693   0.02044   0.01570  -0.0603   0.8096   0.0230
  -1.750   0.1928   0.01896   0.01408  -0.0597   0.7943   0.0238
  -1.500   0.2179   0.01781   0.01274  -0.0590   0.7781   0.0251
  -1.250   0.2473   0.01835   0.01286  -0.0574   0.7595   0.0280
  -1.000   0.2713   0.01605   0.01034  -0.0566   0.7402   0.0288
  -0.750   0.2955   0.01476   0.00896  -0.0561   0.7154   0.0299
  -0.500   0.3202   0.01404   0.00802  -0.0552   0.6812   0.0319
  -0.250   0.3463   0.01494   0.00847  -0.0538   0.6345   0.0351
   0.000   0.0669   0.05082   0.04774  -0.0022   0.6831   0.0348
   0.250   0.3937   0.01267   0.00578  -0.0523   0.5530   0.0404
   0.500   0.4190   0.01240   0.00524  -0.0515   0.5221   0.0459
   0.750   0.4439   0.01193   0.00468  -0.0510   0.4938   0.0509
   1.000   0.4688   0.01151   0.00414  -0.0504   0.4668   0.0620
   1.250   0.4937   0.01116   0.00369  -0.0499   0.4415   0.0756
   1.500   0.5189   0.01084   0.00331  -0.0494   0.4203   0.0869
   1.750   0.5444   0.01063   0.00304  -0.0487   0.4007   0.0878
   2.250   0.5964   0.01059   0.00278  -0.0472   0.3617   0.0622
   2.500   0.6228   0.01081   0.00286  -0.0467   0.3411   0.0551
   2.750   0.6476   0.01071   0.00268  -0.0460   0.3219   0.0530
   3.000   0.6731   0.01074   0.00264  -0.0455   0.3035   0.0521
   3.250   0.6987   0.01084   0.00264  -0.0450   0.2877   0.0494
   3.500   0.7243   0.01096   0.00269  -0.0445   0.2746   0.0477
   3.750   0.7499   0.01110   0.00276  -0.0440   0.2637   0.0470
   4.000   0.7757   0.01122   0.00284  -0.0436   0.2541   0.0475
   4.250   0.8014   0.01137   0.00294  -0.0432   0.2459   0.0493
   4.500   0.8270   0.01156   0.00307  -0.0428   0.2378   0.0516
   4.750   0.8529   0.01171   0.00322  -0.0424   0.2307   0.0592
   5.250   0.9227   0.01054   0.00384  -0.0463   0.2150   1.0000
   5.500   0.9470   0.01084   0.00407  -0.0457   0.2079   1.0000
   5.750   0.9724   0.01103   0.00428  -0.0452   0.2015   1.0000
   6.000   0.9968   0.01133   0.00454  -0.0446   0.1942   1.0000
   6.250   1.0219   0.01154   0.00478  -0.0441   0.1876   1.0000
   6.500   1.0462   0.01184   0.00504  -0.0436   0.1804   1.0000
   6.750   1.0712   0.01205   0.00528  -0.0431   0.1728   1.0000
   7.000   1.0952   0.01238   0.00558  -0.0425   0.1654   1.0000
   7.250   1.1201   0.01260   0.00585  -0.0420   0.1597   1.0000
   7.500   1.1440   0.01292   0.00614  -0.0415   0.1526   1.0000
   7.750   1.1687   0.01316   0.00642  -0.0410   0.1460   1.0000
   8.000   1.1922   0.01350   0.00676  -0.0404   0.1389   1.0000
   8.250   1.2167   0.01375   0.00706  -0.0399   0.1323   1.0000
   8.500   1.2400   0.01411   0.00740  -0.0394   0.1229   1.0000
   8.750   1.2631   0.01449   0.00775  -0.0388   0.1105   1.0000
   9.000   1.2839   0.01516   0.00826  -0.0379   0.0794   1.0000
   9.250   1.2913   0.01742   0.01005  -0.0354   0.0193   1.0000
   9.500   1.3104   0.01826   0.01101  -0.0341   0.0168   1.0000
   9.750   1.3277   0.01927   0.01216  -0.0327   0.0147   1.0000
  10.000   1.3439   0.02034   0.01341  -0.0311   0.0136   1.0000
  10.250   1.3601   0.02131   0.01453  -0.0296   0.0130   1.0000
  10.500   1.3744   0.02239   0.01575  -0.0279   0.0124   1.0000
  10.750   1.3861   0.02360   0.01709  -0.0259   0.0118   1.0000
  11.000   1.3953   0.02489   0.01851  -0.0236   0.0113   1.0000
  11.250   1.3992   0.02635   0.02009  -0.0208   0.0108   1.0000
  11.500   1.3950   0.02798   0.02183  -0.0169   0.0103   1.0000
  11.750   1.3876   0.02996   0.02395  -0.0134   0.0101   1.0000
  12.000   1.3764   0.03251   0.02663  -0.0106   0.0099   1.0000
  12.250   1.3600   0.03602   0.03031  -0.0088   0.0097   1.0000
  12.500   1.3555   0.03889   0.03331  -0.0083   0.0095   1.0000
  12.750   1.3516   0.04199   0.03654  -0.0083   0.0095   1.0000
  13.000   1.3470   0.04546   0.04014  -0.0089   0.0094   1.0000
  13.250   1.3424   0.04924   0.04406  -0.0099   0.0093   1.0000
  13.500   1.3374   0.05332   0.04827  -0.0114   0.0092   1.0000
  13.750   1.3320   0.05771   0.05279  -0.0133   0.0090   1.0000
  14.000   1.3243   0.06244   0.05764  -0.0151   0.0089   1.0000
  14.250   1.3158   0.06721   0.06253  -0.0169   0.0089   1.0000
  14.500   1.3077   0.07204   0.06747  -0.0187   0.0088   1.0000
  14.750   1.2994   0.07688   0.07243  -0.0206   0.0088   1.0000
  15.000   1.2912   0.08190   0.07756  -0.0226   0.0087   1.0000
  15.250   1.2834   0.08697   0.08274  -0.0248   0.0086   1.0000
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