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GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 457 AIRFOIL (goe457-il)
Reynolds number: 200,000
Max Cl/Cd: 73.57 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe457-il-200000.txt
Download as CSV file: xf-goe457-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3619   0.08947   0.08615  -0.0206   1.0000   0.0396
  -7.250  -0.3716   0.08777   0.08452  -0.0186   1.0000   0.0404
  -7.000  -0.3798   0.08580   0.08261  -0.0173   1.0000   0.0414
  -6.750  -0.3839   0.08337   0.08022  -0.0176   1.0000   0.0424
  -6.500  -0.3842   0.08046   0.07733  -0.0242   1.0000   0.0444
  -6.250  -0.3730   0.07665   0.07343  -0.0319   1.0000   0.0450
  -6.000  -0.3775   0.07189   0.06876  -0.0286   1.0000   0.0459
  -5.750  -0.3743   0.06972   0.06662  -0.0253   1.0000   0.0469
  -5.500  -0.3673   0.06727   0.06418  -0.0245   1.0000   0.0482
  -5.250  -0.3571   0.06440   0.06129  -0.0253   1.0000   0.0500
  -5.000  -0.3175   0.05917   0.05565  -0.0376   1.0000   0.0562
  -4.750  -0.3092   0.05361   0.05009  -0.0382   1.0000   0.0574
  -4.500  -0.3000   0.05145   0.04801  -0.0364   0.9999   0.0587
  -4.250  -0.2529   0.04832   0.04463  -0.0432   0.9955   0.0680
  -4.000  -0.2164   0.04271   0.03881  -0.0489   0.9911   0.0716
  -3.750  -0.1809   0.04014   0.03619  -0.0522   0.9863   0.0760
  -3.500  -0.1352   0.03554   0.03110  -0.0581   0.9817   0.0857
  -3.250  -0.0995   0.03354   0.02906  -0.0607   0.9758   0.0934
  -3.000  -0.0564   0.03037   0.02559  -0.0650   0.9718   0.1031
  -2.750  -0.0204   0.02804   0.02295  -0.0673   0.9647   0.1160
  -2.500   0.0276   0.02183   0.01544  -0.0685   0.9615   0.0669
  -2.250   0.0722   0.01950   0.01272  -0.0714   0.9580   0.0642
  -2.000   0.1072   0.01818   0.01113  -0.0723   0.9495   0.0649
  -1.750   0.1531   0.01699   0.00971  -0.0753   0.9448   0.0666
  -1.500   0.1892   0.01597   0.00857  -0.0763   0.9359   0.0675
  -1.250   0.2359   0.01503   0.00754  -0.0795   0.9308   0.0691
  -1.000   0.2723   0.01391   0.00651  -0.0807   0.9213   0.0737
  -0.750   0.3212   0.01306   0.00570  -0.0844   0.9156   0.0811
  -0.500   0.3567   0.01223   0.00496  -0.0852   0.9029   0.0908
  -0.250   0.3910   0.01103   0.00427  -0.0861   0.8882   0.2123
   0.000   0.4510   0.00877   0.00398  -0.0923   0.8722   1.0000
   0.250   0.4832   0.00859   0.00361  -0.0924   0.8405   1.0000
   0.500   0.5152   0.00846   0.00324  -0.0924   0.7886   1.0000
   0.750   0.5475   0.00856   0.00291  -0.0925   0.7258   1.0000
   1.000   0.5722   0.00891   0.00286  -0.0914   0.6754   1.0000
   1.250   0.5955   0.00927   0.00291  -0.0902   0.6381   1.0000
   1.500   0.6189   0.00960   0.00300  -0.0890   0.6095   1.0000
   1.750   0.6427   0.00993   0.00312  -0.0880   0.5867   1.0000
   2.000   0.6669   0.01023   0.00327  -0.0871   0.5675   1.0000
   2.250   0.6915   0.01054   0.00343  -0.0863   0.5510   1.0000
   2.500   0.7162   0.01085   0.00362  -0.0856   0.5357   1.0000
   2.750   0.7410   0.01115   0.00383  -0.0849   0.5213   1.0000
   3.000   0.7659   0.01146   0.00404  -0.0842   0.5075   1.0000
   3.250   0.7906   0.01175   0.00426  -0.0834   0.4936   1.0000
   3.500   0.8151   0.01202   0.00446  -0.0827   0.4796   1.0000
   3.750   0.8394   0.01228   0.00468  -0.0819   0.4653   1.0000
   4.000   0.8635   0.01251   0.00486  -0.0810   0.4508   1.0000
   4.250   0.8873   0.01273   0.00504  -0.0801   0.4361   1.0000
   4.500   0.9110   0.01293   0.00524  -0.0792   0.4211   1.0000
   4.750   0.9346   0.01314   0.00542  -0.0783   0.4062   1.0000
   5.000   0.9584   0.01337   0.00563  -0.0774   0.3928   1.0000
   5.250   0.9822   0.01363   0.00587  -0.0766   0.3803   1.0000
   5.500   1.0061   0.01386   0.00615  -0.0758   0.3672   1.0000
   5.750   1.0296   0.01410   0.00642  -0.0749   0.3535   1.0000
   6.000   1.0527   0.01436   0.00669  -0.0739   0.3389   1.0000
   6.250   1.0754   0.01463   0.00697  -0.0729   0.3232   1.0000
   6.500   1.0977   0.01493   0.00728  -0.0719   0.3057   1.0000
   6.750   1.1197   0.01522   0.00760  -0.0708   0.2840   1.0000
   7.000   1.1399   0.01563   0.00794  -0.0695   0.2532   1.0000
   7.250   1.1578   0.01629   0.00840  -0.0679   0.2081   1.0000
   7.500   1.1741   0.01721   0.00906  -0.0661   0.1635   1.0000
   7.750   1.1911   0.01812   0.00981  -0.0645   0.1409   1.0000
   8.000   1.2086   0.01895   0.01059  -0.0629   0.1282   1.0000
   8.250   1.2266   0.01971   0.01136  -0.0614   0.1188   1.0000
   8.500   1.2429   0.02058   0.01219  -0.0597   0.1116   1.0000
   8.750   1.2625   0.02115   0.01290  -0.0584   0.1058   1.0000
   9.000   1.2797   0.02187   0.01363  -0.0569   0.0993   1.0000
   9.250   1.2987   0.02242   0.01430  -0.0556   0.0938   1.0000
   9.500   1.3175   0.02293   0.01488  -0.0543   0.0869   1.0000
   9.750   1.3365   0.02342   0.01549  -0.0530   0.0805   1.0000
  10.000   1.3554   0.02391   0.01605  -0.0518   0.0698   1.0000
  10.250   1.3720   0.02453   0.01670  -0.0501   0.0564   1.0000
  10.500   1.3826   0.02552   0.01762  -0.0476   0.0408   1.0000
  10.750   1.3891   0.02674   0.01879  -0.0446   0.0317   1.0000
  11.000   1.3946   0.02801   0.02012  -0.0416   0.0284   1.0000
  11.250   1.3977   0.02946   0.02163  -0.0384   0.0264   1.0000
  11.500   1.3983   0.03111   0.02341  -0.0353   0.0252   1.0000
  11.750   1.3995   0.03277   0.02524  -0.0326   0.0243   1.0000
  12.000   1.3987   0.03467   0.02729  -0.0300   0.0234   1.0000
  12.250   1.3967   0.03678   0.02954  -0.0278   0.0225   1.0000
  12.500   1.3926   0.03923   0.03213  -0.0259   0.0219   1.0000
  12.750   1.3875   0.04196   0.03501  -0.0244   0.0215   1.0000
  13.000   1.3812   0.04509   0.03827  -0.0235   0.0212   1.0000
  13.250   1.3731   0.04869   0.04200  -0.0232   0.0208   1.0000
  13.500   1.3671   0.05232   0.04576  -0.0232   0.0206   1.0000
  13.750   1.3595   0.05634   0.04990  -0.0236   0.0203   1.0000
  14.000   1.3533   0.06032   0.05400  -0.0239   0.0201   1.0000
  14.250   1.3481   0.06425   0.05807  -0.0243   0.0199   1.0000
  14.500   1.3439   0.06817   0.06211  -0.0246   0.0198   1.0000
  14.750   1.3404   0.07213   0.06625  -0.0254   0.0197   1.0000
  15.000   1.3360   0.07632   0.07061  -0.0264   0.0196   1.0000
  15.250   1.3303   0.08084   0.07531  -0.0277   0.0196   1.0000
  15.500   1.3235   0.08565   0.08029  -0.0292   0.0195   1.0000
  15.750   1.3148   0.09088   0.08571  -0.0312   0.0195   1.0000
  16.000   1.3053   0.09643   0.09145  -0.0335   0.0195   1.0000
  16.250   1.2943   0.10240   0.09760  -0.0363   0.0196   1.0000
  16.500   1.2818   0.10883   0.10422  -0.0395   0.0196   1.0000
  16.750   1.2676   0.11585   0.11142  -0.0434   0.0196   1.0000
  17.000   1.2528   0.12323   0.11898  -0.0477   0.0197   1.0000
  17.250   1.2369   0.13113   0.12705  -0.0524   0.0197   1.0000
  17.500   1.2228   0.13899   0.13510  -0.0574   0.0198   1.0000
  17.750   1.2094   0.14712   0.14338  -0.0628   0.0200   1.0000
  18.000   1.1911   0.15714   0.15358  -0.0697   0.0203   1.0000
  18.250   1.0645   0.20810   0.20466  -0.0991   0.0253   1.0000
  18.500   1.0533   0.22286   0.21935  -0.1052   0.0316   1.0000
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