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GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.72 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602m-il-1000000.txt
Download as CSV file: xf-goe602m-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 MOD. AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3056   0.10039   0.09891  -0.0340   1.0000   0.0128
 -10.250  -0.3013   0.09531   0.09382  -0.0365   0.9994   0.0128
  -9.750  -0.6037   0.02840   0.02607  -0.0947   0.9858   0.0084
  -9.500  -0.5807   0.02334   0.02045  -0.0993   0.9838   0.0088
  -9.250  -0.5577   0.02162   0.01849  -0.1000   0.9799   0.0091
  -9.000  -0.5343   0.01880   0.01525  -0.1014   0.9765   0.0095
  -8.750  -0.5065   0.01677   0.01294  -0.1029   0.9745   0.0102
  -8.500  -0.4736   0.01632   0.01244  -0.1044   0.9734   0.0107
  -8.250  -0.4408   0.01557   0.01157  -0.1059   0.9724   0.0112
  -8.000  -0.4075   0.01478   0.01065  -0.1076   0.9715   0.0118
  -7.750  -0.3761   0.01402   0.00976  -0.1087   0.9698   0.0124
  -7.500  -0.3506   0.01356   0.00920  -0.1083   0.9651   0.0128
  -7.250  -0.3225   0.01226   0.00775  -0.1089   0.9620   0.0140
  -7.000  -0.2903   0.01207   0.00754  -0.1100   0.9597   0.0148
  -6.750  -0.2573   0.01190   0.00734  -0.1111   0.9576   0.0158
  -6.500  -0.2299   0.01173   0.00712  -0.1110   0.9527   0.0168
  -6.250  -0.2022   0.01122   0.00651  -0.1110   0.9478   0.0177
  -6.000  -0.1727   0.01052   0.00576  -0.1116   0.9438   0.0193
  -5.750  -0.1459   0.01038   0.00561  -0.1114   0.9375   0.0205
  -5.500  -0.1173   0.01017   0.00535  -0.1115   0.9317   0.0219
  -5.250  -0.0886   0.01013   0.00526  -0.1115   0.9259   0.0231
  -5.000  -0.0629   0.00961   0.00465  -0.1111   0.9192   0.0243
  -4.750  -0.0366   0.00896   0.00393  -0.1109   0.9133   0.0263
  -4.500  -0.0105   0.00872   0.00366  -0.1105   0.9064   0.0278
  -4.000   0.0437   0.00831   0.00316  -0.1101   0.8935   0.0308
  -3.750   0.0712   0.00814   0.00292  -0.1099   0.8869   0.0316
  -3.500   0.0975   0.00793   0.00268  -0.1095   0.8793   0.0325
  -3.250   0.1239   0.00753   0.00216  -0.1091   0.8721   0.0347
  -3.000   0.1503   0.00731   0.00190  -0.1087   0.8636   0.0370
  -2.750   0.1774   0.00717   0.00171  -0.1084   0.8556   0.0393
  -2.500   0.2042   0.00704   0.00154  -0.1081   0.8462   0.0411
  -2.250   0.2311   0.00695   0.00139  -0.1078   0.8364   0.0427
  -2.000   0.2577   0.00680   0.00123  -0.1074   0.8258   0.0544
  -1.750   0.2833   0.00650   0.00112  -0.1070   0.8138   0.1233
  -1.500   0.3079   0.00609   0.00103  -0.1065   0.8006   0.2394
  -1.250   0.3340   0.00600   0.00101  -0.1060   0.7862   0.2848
  -0.750   0.3861   0.00596   0.00095  -0.1051   0.7546   0.3295
  -0.500   0.4120   0.00595   0.00094  -0.1047   0.7377   0.3509
  -0.250   0.4374   0.00593   0.00094  -0.1041   0.7197   0.3833
   0.000   0.4618   0.00587   0.00096  -0.1034   0.6989   0.4450
   0.250   0.4858   0.00583   0.00103  -0.1026   0.6740   0.5225
   0.500   0.5103   0.00586   0.00108  -0.1018   0.6506   0.5719
   0.750   0.5348   0.00590   0.00112  -0.1011   0.6287   0.6093
   1.000   0.5594   0.00587   0.00116  -0.1004   0.6104   0.6536
   1.250   0.5801   0.00561   0.00126  -0.0988   0.5930   0.8026
   1.500   0.6325   0.00543   0.00136  -0.1043   0.5711   1.0000
   1.750   0.6572   0.00557   0.00141  -0.1036   0.5526   1.0000
   2.000   0.6822   0.00571   0.00148  -0.1029   0.5357   1.0000
   2.250   0.7071   0.00587   0.00155  -0.1023   0.5184   1.0000
   2.500   0.7319   0.00603   0.00164  -0.1016   0.5008   1.0000
   3.000   0.7817   0.00637   0.00183  -0.1004   0.4661   1.0000
   3.250   0.8059   0.00659   0.00195  -0.0997   0.4427   1.0000
   3.500   0.8303   0.00681   0.00208  -0.0990   0.4202   1.0000
   3.750   0.8542   0.00706   0.00222  -0.0982   0.3954   1.0000
   4.000   0.8778   0.00734   0.00237  -0.0974   0.3674   1.0000
   4.250   0.9012   0.00764   0.00254  -0.0966   0.3366   1.0000
   4.500   0.9237   0.00802   0.00275  -0.0957   0.3002   1.0000
   5.000   0.9633   0.00921   0.00340  -0.0929   0.1944   1.0000
   5.250   0.9780   0.01025   0.00396  -0.0908   0.1080   1.0000
   5.500   0.9977   0.01088   0.00441  -0.0894   0.0724   1.0000
   5.750   1.0142   0.01181   0.00505  -0.0874   0.0191   1.0000
   6.000   1.0374   0.01213   0.00542  -0.0865   0.0170   1.0000
   6.250   1.0593   0.01257   0.00588  -0.0854   0.0148   1.0000
   6.500   1.0804   0.01306   0.00644  -0.0842   0.0135   1.0000
   6.750   1.1028   0.01342   0.00684  -0.0832   0.0128   1.0000
   7.000   1.1241   0.01386   0.00732  -0.0820   0.0122   1.0000
   7.250   1.1447   0.01434   0.00784  -0.0808   0.0115   1.0000
   7.500   1.1646   0.01484   0.00838  -0.0794   0.0108   1.0000
   7.750   1.1817   0.01553   0.00912  -0.0776   0.0100   1.0000
   8.000   1.1921   0.01667   0.01038  -0.0746   0.0093   1.0000
   8.250   1.2106   0.01715   0.01091  -0.0730   0.0091   1.0000
   8.500   1.2255   0.01778   0.01159  -0.0708   0.0088   1.0000
   8.750   1.2388   0.01840   0.01227  -0.0683   0.0085   1.0000
   9.000   1.2509   0.01908   0.01301  -0.0657   0.0082   1.0000
   9.250   1.2618   0.01985   0.01383  -0.0629   0.0079   1.0000
   9.500   1.2715   0.02073   0.01478  -0.0601   0.0078   1.0000
   9.750   1.2820   0.02157   0.01568  -0.0576   0.0075   1.0000
  10.000   1.2920   0.02247   0.01664  -0.0551   0.0073   1.0000
  10.250   1.3024   0.02335   0.01755  -0.0528   0.0070   1.0000
  10.500   1.3070   0.02471   0.01896  -0.0499   0.0068   1.0000
  10.750   1.3050   0.02700   0.02134  -0.0464   0.0065   1.0000
  11.000   1.3103   0.02912   0.02356  -0.0439   0.0063   1.0000
  11.250   1.3212   0.02978   0.02431  -0.0421   0.0062   1.0000
  11.500   1.3300   0.03103   0.02566  -0.0403   0.0061   1.0000
  11.750   1.3379   0.03242   0.02716  -0.0385   0.0059   1.0000
  12.000   1.3440   0.03425   0.02910  -0.0366   0.0058   1.0000
  12.250   1.3493   0.03623   0.03120  -0.0348   0.0057   1.0000
  12.500   1.3541   0.03816   0.03326  -0.0332   0.0056   1.0000
  12.750   1.3570   0.04049   0.03573  -0.0315   0.0055   1.0000
  13.000   1.3587   0.04289   0.03827  -0.0301   0.0055   1.0000
  13.250   1.3584   0.04561   0.04114  -0.0287   0.0054   1.0000
  13.500   1.3575   0.04812   0.04377  -0.0277   0.0053   1.0000
  13.750   1.3509   0.05196   0.04782  -0.0266   0.0053   1.0000
  14.000   1.3454   0.05528   0.05129  -0.0261   0.0052   1.0000
  14.250   1.3375   0.05905   0.05522  -0.0260   0.0052   1.0000
  14.500   1.3224   0.06426   0.06066  -0.0263   0.0053   1.0000
  14.750   1.3135   0.06843   0.06496  -0.0271   0.0052   1.0000
  15.000   1.3017   0.07337   0.07005  -0.0285   0.0051   1.0000
  15.250   1.2803   0.08036   0.07727  -0.0308   0.0052   1.0000
  15.500   1.2619   0.08716   0.08425  -0.0336   0.0053   1.0000
  15.750   1.2498   0.09309   0.09032  -0.0366   0.0051   1.0000
  16.000   1.2336   0.10020   0.09758  -0.0404   0.0051   1.0000
  16.250   1.2076   0.10980   0.10738  -0.0456   0.0053   1.0000
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