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GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 623 AIRFOIL (goe623-il)
Reynolds number: 200,000
Max Cl/Cd: 75.38 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe623-il-200000.txt
Download as CSV file: xf-goe623-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 623 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4063   0.08806   0.08481  -0.0468   1.0000   0.0732
  -8.500  -0.4382   0.08596   0.08282  -0.0454   1.0000   0.0733
  -8.250  -0.4690   0.08355   0.08043  -0.0439   1.0000   0.0734
  -8.000  -0.4732   0.07898   0.07593  -0.0420   0.9992   0.0742
  -7.750  -0.4495   0.07744   0.07443  -0.0390   0.9974   0.0755
  -7.500  -0.4243   0.07445   0.07140  -0.0413   0.9940   0.0777
  -7.000  -0.4150   0.04184   0.03723  -0.0717   0.9732   0.0628
  -6.750  -0.3989   0.03181   0.02601  -0.0736   0.9670   0.0524
  -6.500  -0.3699   0.02821   0.02202  -0.0753   0.9617   0.0531
  -6.250  -0.3328   0.02611   0.01975  -0.0780   0.9585   0.0548
  -6.000  -0.2984   0.02400   0.01730  -0.0797   0.9539   0.0555
  -5.750  -0.2640   0.02238   0.01542  -0.0812   0.9483   0.0567
  -5.500  -0.2249   0.02109   0.01388  -0.0834   0.9447   0.0591
  -5.250  -0.1863   0.01982   0.01237  -0.0854   0.9412   0.0607
  -5.000  -0.1564   0.01894   0.01132  -0.0856   0.9329   0.0618
  -4.750  -0.1210   0.01746   0.00983  -0.0870   0.9282   0.0646
  -4.500  -0.0921   0.01679   0.00916  -0.0871   0.9196   0.0679
  -4.250  -0.0598   0.01606   0.00836  -0.0876   0.9131   0.0712
  -4.000  -0.0328   0.01538   0.00764  -0.0871   0.9037   0.0748
  -3.750  -0.0036   0.01467   0.00697  -0.0871   0.8961   0.0816
  -3.500   0.0214   0.01413   0.00648  -0.0862   0.8850   0.0941
  -3.250   0.0486   0.01363   0.00616  -0.0857   0.8757   0.1428
  -3.000   0.0751   0.01331   0.00590  -0.0852   0.8655   0.1794
  -2.750   0.1010   0.01310   0.00570  -0.0846   0.8542   0.2028
  -2.500   0.1276   0.01285   0.00547  -0.0841   0.8441   0.2253
  -2.250   0.1540   0.01262   0.00527  -0.0836   0.8331   0.2515
  -2.000   0.1797   0.01236   0.00512  -0.0830   0.8212   0.2830
  -1.750   0.2052   0.01196   0.00496  -0.0825   0.8107   0.3464
  -1.500   0.2274   0.01117   0.00484  -0.0814   0.8004   0.5202
  -1.250   0.2427   0.01034   0.00497  -0.0778   0.7889   0.7838
  -1.000   0.2866   0.01019   0.00498  -0.0795   0.7798   0.9477
  -0.750   0.3491   0.01018   0.00479  -0.0862   0.7700   0.9946
  -0.500   0.3828   0.01020   0.00467  -0.0875   0.7587   1.0000
  -0.250   0.4074   0.01023   0.00455  -0.0868   0.7482   1.0000
   0.000   0.4321   0.01025   0.00441  -0.0860   0.7371   1.0000
   0.250   0.4564   0.01029   0.00435  -0.0853   0.7248   1.0000
   0.500   0.4812   0.01036   0.00430  -0.0846   0.7136   1.0000
   0.750   0.5063   0.01042   0.00423  -0.0839   0.7033   1.0000
   1.000   0.5311   0.01049   0.00419  -0.0831   0.6918   1.0000
   1.250   0.5559   0.01058   0.00419  -0.0824   0.6798   1.0000
   1.500   0.5811   0.01069   0.00419  -0.0818   0.6688   1.0000
   1.750   0.6069   0.01082   0.00419  -0.0812   0.6590   1.0000
   2.000   0.6321   0.01095   0.00428  -0.0806   0.6484   1.0000
   2.250   0.6579   0.01110   0.00435  -0.0801   0.6390   1.0000
   2.500   0.6838   0.01125   0.00443  -0.0797   0.6294   1.0000
   2.750   0.7094   0.01141   0.00456  -0.0792   0.6193   1.0000
   3.000   0.7356   0.01159   0.00465  -0.0788   0.6102   1.0000
   3.250   0.7612   0.01174   0.00481  -0.0783   0.6000   1.0000
   3.500   0.7870   0.01191   0.00495  -0.0779   0.5900   1.0000
   3.750   0.8131   0.01209   0.00504  -0.0775   0.5799   1.0000
   4.000   0.8382   0.01223   0.00521  -0.0769   0.5679   1.0000
   4.250   0.8635   0.01239   0.00537  -0.0764   0.5561   1.0000
   4.500   0.8889   0.01255   0.00551  -0.0758   0.5444   1.0000
   4.750   0.9141   0.01272   0.00565  -0.0753   0.5318   1.0000
   5.000   0.9388   0.01288   0.00580  -0.0746   0.5176   1.0000
   5.250   0.9630   0.01305   0.00596  -0.0739   0.5016   1.0000
   5.500   0.9867   0.01322   0.00615  -0.0731   0.4826   1.0000
   5.750   1.0097   0.01342   0.00634  -0.0722   0.4606   1.0000
   6.000   1.0319   0.01369   0.00654  -0.0712   0.4358   1.0000
   6.250   1.0529   0.01405   0.00680  -0.0700   0.4074   1.0000
   6.500   1.0728   0.01454   0.00715  -0.0686   0.3789   1.0000
   6.750   1.0925   0.01511   0.00759  -0.0674   0.3535   1.0000
   7.000   1.1118   0.01578   0.00810  -0.0661   0.3338   1.0000
   7.250   1.1319   0.01643   0.00865  -0.0649   0.3177   1.0000
   7.500   1.1527   0.01705   0.00923  -0.0639   0.3040   1.0000
   7.750   1.1741   0.01763   0.00981  -0.0630   0.2925   1.0000
   8.000   1.1955   0.01826   0.01041  -0.0622   0.2831   1.0000
   8.250   1.2165   0.01887   0.01099  -0.0612   0.2740   1.0000
   8.500   1.2373   0.01939   0.01158  -0.0603   0.2646   1.0000
   8.750   1.2570   0.02001   0.01215  -0.0592   0.2555   1.0000
   9.000   1.2755   0.02046   0.01267  -0.0580   0.2456   1.0000
   9.250   1.2934   0.02099   0.01326  -0.0566   0.2361   1.0000
   9.500   1.3105   0.02161   0.01383  -0.0552   0.2276   1.0000
   9.750   1.3275   0.02205   0.01443  -0.0538   0.2193   1.0000
  10.000   1.3421   0.02271   0.01506  -0.0520   0.2121   1.0000
  10.250   1.3563   0.02316   0.01571  -0.0501   0.2042   1.0000
  10.500   1.3682   0.02385   0.01642  -0.0480   0.1963   1.0000
  10.750   1.3797   0.02446   0.01715  -0.0461   0.1859   1.0000
  11.000   1.3906   0.02519   0.01799  -0.0442   0.1735   1.0000
  11.250   1.3981   0.02618   0.01901  -0.0422   0.1558   1.0000
  11.500   1.3972   0.02799   0.02059  -0.0398   0.1005   1.0000
  11.750   1.3803   0.03137   0.02357  -0.0364   0.0649   1.0000
  12.000   1.3713   0.03434   0.02654  -0.0340   0.0549   1.0000
  12.250   1.3614   0.03755   0.02979  -0.0321   0.0499   1.0000
  12.500   1.3600   0.04014   0.03252  -0.0308   0.0461   1.0000
  12.750   1.3538   0.04328   0.03575  -0.0298   0.0434   1.0000
  13.000   1.3414   0.04721   0.03974  -0.0290   0.0416   1.0000
  13.250   1.3407   0.05006   0.04273  -0.0285   0.0399   1.0000
  13.500   1.3375   0.05323   0.04602  -0.0281   0.0384   1.0000
  13.750   1.3338   0.05654   0.04942  -0.0278   0.0371   1.0000
  14.000   1.3293   0.05998   0.05292  -0.0277   0.0359   1.0000
  14.250   1.3236   0.06350   0.05645  -0.0274   0.0348   1.0000
  14.500   1.3216   0.06661   0.05962  -0.0269   0.0337   1.0000
  14.750   1.3224   0.06961   0.06276  -0.0269   0.0327   1.0000
  15.000   1.3230   0.07265   0.06591  -0.0269   0.0316   1.0000
  15.250   1.3238   0.07564   0.06898  -0.0269   0.0307   1.0000
  15.500   1.3255   0.07848   0.07187  -0.0268   0.0299   1.0000
  15.750   1.3288   0.08099   0.07440  -0.0264   0.0291   1.0000
  16.000   1.3377   0.08241   0.07578  -0.0246   0.0282   1.0000
  16.250   1.3418   0.08498   0.07847  -0.0240   0.0277   1.0000
  16.500   1.3408   0.08851   0.08219  -0.0245   0.0273   1.0000
  16.750   1.3388   0.09220   0.08607  -0.0252   0.0268   1.0000
  17.000   1.3360   0.09606   0.09009  -0.0260   0.0264   1.0000
  17.250   1.3322   0.10014   0.09434  -0.0271   0.0259   1.0000
  17.500   1.3280   0.10435   0.09871  -0.0284   0.0254   1.0000
  17.750   1.3236   0.10866   0.10318  -0.0299   0.0250   1.0000
  18.000   1.3188   0.11308   0.10774  -0.0316   0.0247   1.0000
  18.250   1.3124   0.11788   0.11270  -0.0335   0.0245   1.0000
  18.500   1.3040   0.12319   0.11819  -0.0360   0.0243   1.0000
  18.750   1.2939   0.12902   0.12420  -0.0389   0.0242   1.0000
  19.000   1.2815   0.13553   0.13091  -0.0426   0.0242   1.0000
  19.250   1.2624   0.14383   0.13946  -0.0478   0.0243   1.0000
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