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GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 457 AIRFOIL (goe457-il)
Reynolds number: 500,000
Max Cl/Cd: 98.78 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe457-il-500000.txt
Download as CSV file: xf-goe457-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 457 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3845   0.09137   0.08925  -0.0222   1.0000   0.0210
  -7.750  -0.3986   0.08989   0.08782  -0.0194   1.0000   0.0210
  -7.500  -0.4079   0.08771   0.08568  -0.0182   1.0000   0.0210
  -7.250  -0.4019   0.08366   0.08164  -0.0216   0.9990   0.0210
  -7.000  -0.3886   0.07790   0.07589  -0.0253   0.9965   0.0216
  -6.750  -0.3644   0.07417   0.07214  -0.0301   0.9943   0.0220
  -6.500  -0.3419   0.07051   0.06846  -0.0348   0.9909   0.0227
  -6.250  -0.3142   0.06596   0.06387  -0.0419   0.9874   0.0238
  -6.000  -0.2641   0.05776   0.05551  -0.0582   0.9843   0.0268
  -5.750  -0.2322   0.05125   0.04885  -0.0657   0.9795   0.0270
  -5.500  -0.2093   0.04337   0.04081  -0.0724   0.9753   0.0281
  -5.250  -0.1770   0.04113   0.03852  -0.0758   0.9731   0.0291
  -5.000  -0.1392   0.03738   0.03461  -0.0808   0.9714   0.0312
  -4.750  -0.1063   0.03305   0.02976  -0.0828   0.9651   0.0350
  -4.500  -0.0814   0.02693   0.02341  -0.0861   0.9618   0.0372
  -4.250  -0.0465   0.02585   0.02227  -0.0884   0.9599   0.0402
  -4.000  -0.0101   0.01853   0.01380  -0.0902   0.9581   0.0357
  -3.750   0.0127   0.01621   0.01117  -0.0893   0.9520   0.0363
  -3.500   0.0472   0.01443   0.00912  -0.0905   0.9490   0.0365
  -3.250   0.0843   0.01306   0.00758  -0.0923   0.9466   0.0374
  -3.000   0.1222   0.01226   0.00671  -0.0943   0.9441   0.0392
  -2.750   0.1484   0.01151   0.00587  -0.0936   0.9366   0.0399
  -2.500   0.1832   0.01071   0.00499  -0.0947   0.9315   0.0406
  -2.250   0.2129   0.01012   0.00433  -0.0947   0.9236   0.0414
  -2.000   0.2465   0.00961   0.00378  -0.0956   0.9156   0.0430
  -1.750   0.2742   0.00921   0.00333  -0.0951   0.9038   0.0440
  -1.500   0.3026   0.00887   0.00293  -0.0949   0.8904   0.0447
  -1.250   0.3300   0.00849   0.00249  -0.0944   0.8739   0.0459
  -1.000   0.3564   0.00820   0.00214  -0.0937   0.8514   0.0482
  -0.750   0.3824   0.00805   0.00189  -0.0929   0.8134   0.0515
  -0.500   0.4058   0.00814   0.00166  -0.0914   0.7422   0.0560
  -0.250   0.4265   0.00832   0.00159  -0.0896   0.6794   0.0731
   0.000   0.4477   0.00837   0.00156  -0.0881   0.6263   0.1275
   0.250   0.4689   0.00825   0.00164  -0.0868   0.5869   0.2680
   0.500   0.4904   0.00801   0.00173  -0.0856   0.5606   0.4411
   0.750   0.5430   0.00694   0.00187  -0.0912   0.5377   1.0000
   1.000   0.5673   0.00711   0.00192  -0.0903   0.5226   1.0000
   1.250   0.5919   0.00728   0.00197  -0.0895   0.5092   1.0000
   1.500   0.6167   0.00745   0.00204  -0.0887   0.4967   1.0000
   1.750   0.6415   0.00762   0.00211  -0.0879   0.4851   1.0000
   2.000   0.6669   0.00775   0.00218  -0.0873   0.4734   1.0000
   2.250   0.6920   0.00789   0.00225  -0.0866   0.4608   1.0000
   2.500   0.7172   0.00804   0.00233  -0.0859   0.4488   1.0000
   2.750   0.7422   0.00819   0.00243  -0.0852   0.4370   1.0000
   3.000   0.7672   0.00835   0.00251  -0.0845   0.4222   1.0000
   3.250   0.7922   0.00851   0.00260  -0.0839   0.4061   1.0000
   3.500   0.8172   0.00867   0.00271  -0.0832   0.3929   1.0000
   3.750   0.8422   0.00884   0.00283  -0.0825   0.3810   1.0000
   4.000   0.8673   0.00901   0.00296  -0.0819   0.3677   1.0000
   4.250   0.8922   0.00920   0.00309  -0.0813   0.3536   1.0000
   4.500   0.9169   0.00940   0.00325  -0.0806   0.3391   1.0000
   4.750   0.9418   0.00960   0.00342  -0.0800   0.3260   1.0000
   5.000   0.9665   0.00981   0.00359  -0.0793   0.3135   1.0000
   5.250   0.9911   0.01004   0.00378  -0.0787   0.3005   1.0000
   5.500   1.0155   0.01028   0.00400  -0.0780   0.2861   1.0000
   5.750   1.0394   0.01056   0.00422  -0.0772   0.2675   1.0000
   6.000   1.0627   0.01091   0.00446  -0.0764   0.2437   1.0000
   6.250   1.0854   0.01132   0.00475  -0.0755   0.2162   1.0000
   6.500   1.1064   0.01191   0.00513  -0.0744   0.1739   1.0000
   6.750   1.1252   0.01274   0.00567  -0.0730   0.1270   1.0000
   7.000   1.1462   0.01333   0.00617  -0.0719   0.1093   1.0000
   7.500   1.1902   0.01425   0.00704  -0.0700   0.0897   1.0000
   7.750   1.2122   0.01467   0.00746  -0.0690   0.0823   1.0000
   8.000   1.2344   0.01507   0.00785  -0.0681   0.0756   1.0000
   8.250   1.2566   0.01545   0.00823  -0.0672   0.0688   1.0000
   8.500   1.2778   0.01592   0.00865  -0.0662   0.0592   1.0000
   8.750   1.2983   0.01643   0.00910  -0.0650   0.0474   1.0000
   9.250   1.3287   0.01834   0.01084  -0.0611   0.0177   1.0000
   9.500   1.3451   0.01913   0.01172  -0.0592   0.0161   1.0000
   9.750   1.3606   0.01995   0.01267  -0.0572   0.0150   1.0000
  10.000   1.3760   0.02071   0.01355  -0.0553   0.0143   1.0000
  10.250   1.3893   0.02155   0.01449  -0.0530   0.0137   1.0000
  10.500   1.3983   0.02249   0.01554  -0.0500   0.0131   1.0000
  10.750   1.4052   0.02351   0.01666  -0.0469   0.0127   1.0000
  11.000   1.4098   0.02467   0.01791  -0.0435   0.0124   1.0000
  11.250   1.4113   0.02603   0.01939  -0.0400   0.0121   1.0000
  11.500   1.4098   0.02764   0.02111  -0.0364   0.0118   1.0000
  11.750   1.4038   0.02965   0.02324  -0.0328   0.0115   1.0000
  12.000   1.3950   0.03207   0.02578  -0.0294   0.0113   1.0000
  12.250   1.3934   0.03413   0.02795  -0.0271   0.0112   1.0000
  12.500   1.3949   0.03605   0.02999  -0.0254   0.0110   1.0000
  12.750   1.3952   0.03822   0.03227  -0.0239   0.0109   1.0000
  13.000   1.3988   0.04020   0.03438  -0.0231   0.0106   1.0000
  13.250   1.3963   0.04300   0.03731  -0.0224   0.0104   1.0000
  13.500   1.3937   0.04602   0.04045  -0.0221   0.0103   1.0000
  13.750   1.3907   0.04931   0.04386  -0.0222   0.0100   1.0000
  14.000   1.3866   0.05290   0.04758  -0.0227   0.0099   1.0000
  14.250   1.3821   0.05670   0.05151  -0.0234   0.0098   1.0000
  14.500   1.3777   0.06063   0.05555  -0.0244   0.0096   1.0000
  14.750   1.3727   0.06472   0.05975  -0.0255   0.0095   1.0000
  15.000   1.3671   0.06898   0.06413  -0.0267   0.0094   1.0000
  15.250   1.3616   0.07331   0.06858  -0.0280   0.0093   1.0000
  15.500   1.3554   0.07784   0.07323  -0.0295   0.0093   1.0000
  15.750   1.3488   0.08251   0.07800  -0.0313   0.0091   1.0000
  16.000   1.3421   0.08734   0.08295  -0.0331   0.0091   1.0000
  16.250   1.3349   0.09233   0.08807  -0.0351   0.0091   1.0000
  16.500   1.3273   0.09755   0.09341  -0.0374   0.0091   1.0000
  16.750   1.3194   0.10297   0.09895  -0.0399   0.0090   1.0000
  17.000   1.3114   0.10852   0.10462  -0.0426   0.0089   1.0000
  17.250   1.3027   0.11434   0.11056  -0.0456   0.0089   1.0000
  17.500   1.2933   0.12051   0.11687  -0.0488   0.0089   1.0000
  17.750   1.2840   0.12684   0.12334  -0.0524   0.0089   1.0000
  18.000   1.2740   0.13341   0.13005  -0.0562   0.0089   1.0000
  18.250   1.2634   0.14033   0.13711  -0.0603   0.0089   1.0000
  18.500   1.2526   0.14749   0.14440  -0.0647   0.0089   1.0000
  18.750   1.2406   0.15520   0.15225  -0.0696   0.0090   1.0000
  19.000   1.2158   0.16707   0.16437  -0.0774   0.0093   1.0000
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