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GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 550 AIRFOIL (goe550-il)
Reynolds number: 200,000
Max Cl/Cd: 75.29 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe550-il-200000-n5.txt
Download as CSV file: xf-goe550-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 550 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6474   0.07927   0.07499  -0.0651   1.0000   0.0414
 -13.250  -0.7026   0.06806   0.06364  -0.0717   1.0000   0.0413
 -13.000  -0.7391   0.06050   0.05597  -0.0759   1.0000   0.0413
 -12.750  -0.7700   0.05426   0.04965  -0.0789   1.0000   0.0414
 -12.500  -0.8010   0.04863   0.04395  -0.0811   1.0000   0.0415
 -12.250  -0.8370   0.04361   0.03891  -0.0820   1.0000   0.0413
 -12.000  -0.8598   0.03806   0.03315  -0.0858   1.0000   0.0415
 -11.750  -0.8672   0.03528   0.03014  -0.0855   1.0000   0.0422
 -11.500  -0.8555   0.03323   0.02800  -0.0866   0.9981   0.0432
 -11.250  -0.8269   0.03146   0.02613  -0.0900   0.9939   0.0447
 -11.000  -0.7997   0.02987   0.02438  -0.0926   0.9892   0.0465
 -10.750  -0.7703   0.02832   0.02260  -0.0953   0.9848   0.0484
 -10.500  -0.7427   0.02690   0.02092  -0.0972   0.9799   0.0500
 -10.250  -0.7149   0.02562   0.01962  -0.0988   0.9749   0.0518
 -10.000  -0.6833   0.02459   0.01849  -0.1009   0.9712   0.0538
  -9.750  -0.6574   0.02361   0.01737  -0.1016   0.9644   0.0557
  -9.500  -0.6257   0.02263   0.01619  -0.1032   0.9604   0.0578
  -9.250  -0.5989   0.02168   0.01517  -0.1039   0.9541   0.0599
  -9.000  -0.5690   0.02087   0.01430  -0.1050   0.9487   0.0622
  -8.750  -0.5355   0.02008   0.01341  -0.1067   0.9453   0.0648
  -8.500  -0.5093   0.01941   0.01260  -0.1068   0.9374   0.0673
  -8.250  -0.4771   0.01868   0.01183  -0.1081   0.9326   0.0706
  -8.000  -0.4436   0.01808   0.01116  -0.1096   0.9279   0.0746
  -7.750  -0.4144   0.01755   0.01049  -0.1100   0.9199   0.0785
  -7.500  -0.3794   0.01694   0.00987  -0.1117   0.9151   0.0833
  -7.250  -0.3496   0.01650   0.00932  -0.1122   0.9071   0.0889
  -7.000  -0.3162   0.01599   0.00878  -0.1135   0.9009   0.0951
  -6.750  -0.2833   0.01559   0.00825  -0.1145   0.8944   0.1021
  -6.500  -0.2520   0.01515   0.00779  -0.1153   0.8867   0.1085
  -6.250  -0.2176   0.01478   0.00731  -0.1167   0.8805   0.1161
  -6.000  -0.1882   0.01443   0.00695  -0.1170   0.8717   0.1231
  -5.750  -0.1544   0.01412   0.00654  -0.1182   0.8651   0.1310
  -5.500  -0.1260   0.01387   0.00629  -0.1183   0.8557   0.1384
  -5.250  -0.0937   0.01364   0.00598  -0.1190   0.8486   0.1469
  -5.000  -0.0658   0.01349   0.00581  -0.1190   0.8392   0.1553
  -4.750  -0.0349   0.01335   0.00560  -0.1194   0.8317   0.1642
  -4.500  -0.0072   0.01326   0.00543  -0.1192   0.8226   0.1737
  -4.250   0.0228   0.01320   0.00535  -0.1195   0.8149   0.1832
  -4.000   0.0499   0.01316   0.00525  -0.1192   0.8058   0.1924
  -3.750   0.0793   0.01313   0.00513  -0.1193   0.7984   0.2005
  -3.500   0.1061   0.01306   0.00499  -0.1189   0.7895   0.2068
  -3.000   0.1615   0.01299   0.00479  -0.1184   0.7729   0.2198
  -2.750   0.1897   0.01293   0.00468  -0.1183   0.7654   0.2248
  -2.500   0.2162   0.01289   0.00462  -0.1178   0.7564   0.2298
  -2.250   0.2442   0.01286   0.00448  -0.1176   0.7485   0.2352
  -2.000   0.2706   0.01280   0.00440  -0.1172   0.7391   0.2396
  -1.750   0.2975   0.01276   0.00432  -0.1168   0.7288   0.2443
  -1.500   0.3239   0.01273   0.00423  -0.1162   0.7169   0.2497
  -1.250   0.3502   0.01272   0.00414  -0.1157   0.7050   0.2546
  -1.000   0.3767   0.01266   0.00407  -0.1152   0.6951   0.2588
  -0.750   0.4031   0.01264   0.00404  -0.1147   0.6852   0.2642
  -0.500   0.4298   0.01266   0.00400  -0.1143   0.6757   0.2706
  -0.250   0.4562   0.01262   0.00397  -0.1138   0.6663   0.2765
   0.000   0.4824   0.01262   0.00396  -0.1133   0.6565   0.2824
   0.250   0.5089   0.01263   0.00391  -0.1129   0.6471   0.2872
   0.500   0.5347   0.01259   0.00391  -0.1123   0.6367   0.2913
   0.750   0.5607   0.01258   0.00390  -0.1118   0.6271   0.2961
   1.000   0.5868   0.01260   0.00390  -0.1113   0.6174   0.3019
   1.250   0.6125   0.01260   0.00393  -0.1107   0.6072   0.3078
   1.500   0.6381   0.01263   0.00395  -0.1101   0.5973   0.3146
   1.750   0.6637   0.01266   0.00400  -0.1095   0.5869   0.3216
   2.000   0.6892   0.01269   0.00406  -0.1089   0.5773   0.3297
   2.250   0.7145   0.01274   0.00413  -0.1083   0.5677   0.3395
   2.500   0.7396   0.01278   0.00423  -0.1076   0.5574   0.3527
   2.750   0.7643   0.01282   0.00434  -0.1069   0.5474   0.3728
   3.000   0.7887   0.01283   0.00450  -0.1062   0.5370   0.4109
   3.250   0.8129   0.01283   0.00466  -0.1054   0.5273   0.4714
   3.500   0.8365   0.01280   0.00481  -0.1045   0.5178   0.5382
   4.000   0.8977   0.01233   0.00520  -0.1052   0.4934   1.0000
   4.250   0.9211   0.01256   0.00535  -0.1042   0.4815   1.0000
   4.500   0.9443   0.01278   0.00553  -0.1032   0.4693   1.0000
   4.750   0.9678   0.01301   0.00573  -0.1023   0.4577   1.0000
   5.000   0.9907   0.01325   0.00594  -0.1012   0.4463   1.0000
   5.250   1.0131   0.01352   0.00616  -0.1001   0.4351   1.0000
   5.500   1.0357   0.01377   0.00640  -0.0991   0.4231   1.0000
   5.750   1.0578   0.01405   0.00665  -0.0979   0.4115   1.0000
   6.000   1.0794   0.01435   0.00693  -0.0967   0.4010   1.0000
   6.250   1.1010   0.01465   0.00721  -0.0955   0.3903   1.0000
   6.500   1.1224   0.01496   0.00752  -0.0943   0.3804   1.0000
   6.750   1.1430   0.01531   0.00784  -0.0930   0.3715   1.0000
   7.000   1.1646   0.01562   0.00819  -0.0918   0.3628   1.0000
   7.250   1.1843   0.01600   0.00854  -0.0903   0.3543   1.0000
   7.500   1.2035   0.01636   0.00891  -0.0888   0.3427   1.0000
   7.750   1.2209   0.01677   0.00930  -0.0869   0.3296   1.0000
   8.000   1.2365   0.01719   0.00971  -0.0848   0.3163   1.0000
   8.250   1.2510   0.01764   0.01014  -0.0825   0.3037   1.0000
   8.500   1.2655   0.01810   0.01059  -0.0802   0.2916   1.0000
   8.750   1.2810   0.01855   0.01107  -0.0781   0.2791   1.0000
   9.000   1.2951   0.01905   0.01160  -0.0759   0.2654   1.0000
   9.250   1.3075   0.01963   0.01217  -0.0735   0.2491   1.0000
   9.500   1.3171   0.02035   0.01283  -0.0708   0.2285   1.0000
   9.750   1.3228   0.02129   0.01365  -0.0678   0.1993   1.0000
  10.000   1.3238   0.02257   0.01474  -0.0643   0.1669   1.0000
  10.750   1.3313   0.02676   0.01870  -0.0560   0.1178   1.0000
  11.000   1.3366   0.02813   0.02008  -0.0539   0.1095   1.0000
  11.250   1.3416   0.02958   0.02155  -0.0519   0.1012   1.0000
  11.500   1.3483   0.03098   0.02301  -0.0502   0.0934   1.0000
  11.750   1.3527   0.03260   0.02465  -0.0485   0.0847   1.0000
  12.000   1.3576   0.03426   0.02635  -0.0471   0.0760   1.0000
  12.250   1.3607   0.03612   0.02822  -0.0456   0.0679   1.0000
  12.500   1.3625   0.03818   0.03029  -0.0443   0.0619   1.0000
  12.750   1.3636   0.04039   0.03253  -0.0431   0.0567   1.0000
  13.000   1.3642   0.04271   0.03490  -0.0421   0.0527   1.0000
  13.250   1.3647   0.04515   0.03740  -0.0413   0.0488   1.0000
  13.500   1.3626   0.04795   0.04024  -0.0406   0.0458   1.0000
  13.750   1.3639   0.05048   0.04288  -0.0400   0.0429   1.0000
  14.000   1.3625   0.05339   0.04587  -0.0397   0.0403   1.0000
  14.250   1.3594   0.05662   0.04916  -0.0395   0.0384   1.0000
  14.500   1.3593   0.05960   0.05226  -0.0394   0.0364   1.0000
  14.750   1.3575   0.06287   0.05562  -0.0396   0.0345   1.0000
  15.000   1.3537   0.06650   0.05932  -0.0399   0.0331   1.0000
  15.250   1.3503   0.07018   0.06309  -0.0404   0.0317   1.0000
  15.500   1.3487   0.07370   0.06673  -0.0409   0.0302   1.0000
  15.750   1.3459   0.07746   0.07059  -0.0416   0.0289   1.0000
  16.000   1.3415   0.08153   0.07474  -0.0425   0.0280   1.0000
  16.250   1.3351   0.08600   0.07928  -0.0437   0.0271   1.0000
  16.500   1.3332   0.08984   0.08326  -0.0446   0.0262   1.0000
  16.750   1.3303   0.09389   0.08743  -0.0458   0.0253   1.0000
  17.000   1.3270   0.09807   0.09171  -0.0471   0.0245   1.0000
  17.250   1.3235   0.10235   0.09609  -0.0485   0.0238   1.0000
  17.500   1.3195   0.10676   0.10057  -0.0501   0.0232   1.0000
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