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GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 413 AIRFOIL (goe413-il)
Reynolds number: 500,000
Max Cl/Cd: 108.28 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe413-il-500000.txt
Download as CSV file: xf-goe413-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 413 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6427   0.04945   0.04582  -0.0967   0.8972   0.0489
 -11.500  -0.6531   0.04456   0.04071  -0.1018   0.8865   0.0487
 -11.250  -0.6545   0.04083   0.03668  -0.1047   0.8777   0.0486
 -11.000  -0.6482   0.03782   0.03339  -0.1065   0.8705   0.0486
 -10.750  -0.6365   0.03535   0.03064  -0.1078   0.8633   0.0487
 -10.500  -0.6213   0.03339   0.02838  -0.1085   0.8569   0.0488
 -10.250  -0.6027   0.03185   0.02657  -0.1091   0.8509   0.0490
 -10.000  -0.5840   0.02987   0.02431  -0.1097   0.8445   0.0494
  -9.750  -0.5630   0.02759   0.02193  -0.1099   0.8385   0.0498
  -9.500  -0.5392   0.02630   0.02057  -0.1100   0.8324   0.0502
  -9.250  -0.5142   0.02517   0.01940  -0.1101   0.8258   0.0505
  -9.000  -0.4892   0.02414   0.01828  -0.1102   0.8192   0.0508
  -8.750  -0.4639   0.02320   0.01722  -0.1102   0.8131   0.0511
  -8.500  -0.4379   0.02226   0.01621  -0.1103   0.8061   0.0515
  -8.250  -0.4118   0.02140   0.01523  -0.1103   0.7989   0.0519
  -8.000  -0.3853   0.02061   0.01432  -0.1104   0.7917   0.0522
  -7.750  -0.3583   0.01983   0.01346  -0.1104   0.7832   0.0526
  -7.500  -0.3314   0.01917   0.01266  -0.1104   0.7752   0.0531
  -7.250  -0.3036   0.01858   0.01199  -0.1105   0.7660   0.0536
  -7.000  -0.2759   0.01810   0.01137  -0.1104   0.7568   0.0541
  -6.750  -0.2478   0.01762   0.01079  -0.1105   0.7466   0.0545
  -6.500  -0.2199   0.01714   0.01018  -0.1104   0.7359   0.0547
  -6.250  -0.1928   0.01609   0.00915  -0.1105   0.7243   0.0553
  -6.000  -0.1655   0.01542   0.00845  -0.1104   0.7132   0.0558
  -5.750  -0.1375   0.01491   0.00791  -0.1105   0.7017   0.0563
  -5.500  -0.1094   0.01449   0.00744  -0.1105   0.6915   0.0569
  -5.250  -0.0811   0.01411   0.00701  -0.1106   0.6813   0.0576
  -5.000  -0.0527   0.01379   0.00663  -0.1106   0.6723   0.0583
  -4.750  -0.0240   0.01350   0.00629  -0.1107   0.6634   0.0592
  -4.500   0.0046   0.01327   0.00597  -0.1108   0.6560   0.0599
  -4.250   0.0337   0.01303   0.00569  -0.1109   0.6490   0.0604
  -4.000   0.0624   0.01268   0.00530  -0.1111   0.6421   0.0611
  -3.750   0.0911   0.01233   0.00491  -0.1113   0.6359   0.0621
  -3.500   0.1205   0.01205   0.00464  -0.1115   0.6301   0.0631
  -3.250   0.1497   0.01185   0.00441  -0.1117   0.6242   0.0642
  -3.000   0.1789   0.01173   0.00421  -0.1118   0.6184   0.0653
  -2.750   0.2085   0.01157   0.00404  -0.1120   0.6133   0.0666
  -2.500   0.2381   0.01135   0.00382  -0.1123   0.6077   0.0685
  -2.250   0.2674   0.01121   0.00364  -0.1125   0.6022   0.0707
  -2.000   0.2968   0.01115   0.00352  -0.1126   0.5968   0.0732
  -1.750   0.3266   0.01098   0.00339  -0.1128   0.5922   0.0780
  -1.500   0.3561   0.01057   0.00326  -0.1133   0.5874   0.1351
  -1.250   0.3856   0.01047   0.00323  -0.1135   0.5827   0.1703
  -1.000   0.4149   0.01046   0.00326  -0.1137   0.5778   0.1928
  -0.750   0.4446   0.01036   0.00325  -0.1139   0.5737   0.2131
  -0.500   0.4742   0.01029   0.00325  -0.1141   0.5692   0.2308
  -0.250   0.5036   0.01025   0.00325  -0.1143   0.5647   0.2506
   0.000   0.5329   0.01025   0.00328  -0.1145   0.5600   0.2732
   0.250   0.5623   0.01023   0.00332  -0.1147   0.5558   0.2984
   0.500   0.5919   0.01016   0.00337  -0.1149   0.5514   0.3267
   0.750   0.6213   0.01011   0.00341  -0.1151   0.5468   0.3559
   1.250   0.6796   0.01015   0.00352  -0.1154   0.5375   0.4093
   1.500   0.7090   0.01008   0.00358  -0.1156   0.5331   0.4386
   1.750   0.7382   0.01003   0.00365  -0.1157   0.5282   0.4753
   2.000   0.7671   0.01002   0.00373  -0.1158   0.5233   0.5211
   2.250   0.7959   0.01006   0.00384  -0.1159   0.5179   0.5623
   2.500   0.8248   0.01000   0.00391  -0.1160   0.5118   0.5995
   2.750   0.8532   0.00995   0.00396  -0.1159   0.5051   0.6389
   3.000   0.8810   0.00992   0.00408  -0.1158   0.4991   0.6904
   3.250   0.9079   0.00979   0.00420  -0.1154   0.4927   0.7703
   3.500   0.9307   0.00967   0.00428  -0.1139   0.4858   0.8573
   3.750   0.9533   0.00955   0.00428  -0.1124   0.4791   1.0000
   4.000   0.9823   0.00965   0.00436  -0.1125   0.4717   1.0000
   4.250   1.0104   0.00982   0.00445  -0.1125   0.4646   1.0000
   4.500   1.0391   0.00994   0.00456  -0.1126   0.4570   1.0000
   4.750   1.0669   0.01011   0.00467  -0.1126   0.4479   1.0000
   5.000   1.0949   0.01026   0.00480  -0.1126   0.4395   1.0000
   5.250   1.1222   0.01046   0.00494  -0.1125   0.4298   1.0000
   5.500   1.1497   0.01065   0.00510  -0.1124   0.4200   1.0000
   6.000   1.2030   0.01111   0.00546  -0.1121   0.3987   1.0000
   6.250   1.2288   0.01139   0.00568  -0.1118   0.3873   1.0000
   6.500   1.2542   0.01170   0.00593  -0.1114   0.3759   1.0000
   6.750   1.2800   0.01198   0.00617  -0.1111   0.3655   1.0000
   7.000   1.3044   0.01233   0.00646  -0.1107   0.3551   1.0000
   7.250   1.3292   0.01265   0.00676  -0.1102   0.3443   1.0000
   7.500   1.3530   0.01303   0.00708  -0.1097   0.3327   1.0000
   7.750   1.3754   0.01348   0.00746  -0.1089   0.3212   1.0000
   8.000   1.3986   0.01385   0.00781  -0.1083   0.3098   1.0000
   8.250   1.4206   0.01429   0.00821  -0.1075   0.2984   1.0000
   8.500   1.4406   0.01481   0.00866  -0.1065   0.2854   1.0000
   8.750   1.4590   0.01541   0.00918  -0.1052   0.2690   1.0000
   9.000   1.4745   0.01606   0.00976  -0.1036   0.2514   1.0000
   9.250   1.4856   0.01691   0.01049  -0.1013   0.2295   1.0000
   9.500   1.4896   0.01825   0.01163  -0.0985   0.1985   1.0000
   9.750   1.4858   0.02021   0.01334  -0.0953   0.1597   1.0000
  10.000   1.4688   0.02333   0.01611  -0.0916   0.1069   1.0000
  10.250   1.4661   0.02563   0.01829  -0.0894   0.0894   1.0000
  10.500   1.4720   0.02734   0.02000  -0.0879   0.0840   1.0000
  10.750   1.4781   0.02908   0.02176  -0.0866   0.0810   1.0000
  11.000   1.4835   0.03093   0.02363  -0.0853   0.0787   1.0000
  11.250   1.4918   0.03259   0.02535  -0.0843   0.0774   1.0000
  11.500   1.4986   0.03440   0.02722  -0.0833   0.0762   1.0000
  11.750   1.5038   0.03640   0.02927  -0.0824   0.0751   1.0000
  12.000   1.5075   0.03860   0.03153  -0.0815   0.0742   1.0000
  12.250   1.5096   0.04102   0.03400  -0.0806   0.0734   1.0000
  12.500   1.5101   0.04365   0.03669  -0.0798   0.0726   1.0000
  12.750   1.5090   0.04653   0.03964  -0.0792   0.0718   1.0000
  13.000   1.5062   0.04967   0.04285  -0.0786   0.0711   1.0000
  13.250   1.5081   0.05235   0.04560  -0.0781   0.0707   1.0000
  13.500   1.5106   0.05501   0.04834  -0.0778   0.0703   1.0000
  13.750   1.5125   0.05777   0.05117  -0.0774   0.0699   1.0000
  14.000   1.5140   0.06056   0.05403  -0.0771   0.0694   1.0000
  14.250   1.5146   0.06351   0.05706  -0.0769   0.0689   1.0000
  14.500   1.5150   0.06650   0.06012  -0.0767   0.0685   1.0000
  14.750   1.5155   0.06950   0.06318  -0.0765   0.0681   1.0000
  15.000   1.5153   0.07259   0.06634  -0.0764   0.0678   1.0000
  15.250   1.5160   0.07559   0.06940  -0.0763   0.0674   1.0000
  15.500   1.5161   0.07870   0.07257  -0.0763   0.0671   1.0000
  15.750   1.5172   0.08166   0.07558  -0.0762   0.0667   1.0000
  16.000   1.5181   0.08465   0.07863  -0.0762   0.0664   1.0000
  16.250   1.5196   0.08756   0.08159  -0.0762   0.0661   1.0000
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