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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 500,000
Max Cl/Cd: 98.96 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe188-il-500000-n5.txt
Download as CSV file: xf-goe188-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3304   0.09796   0.09584  -0.0220   1.0000   0.0053
  -8.000  -0.3259   0.09482   0.09273  -0.0238   1.0000   0.0053
  -7.750  -0.3210   0.09161   0.08955  -0.0259   0.9964   0.0053
  -7.500  -0.3033   0.08707   0.08499  -0.0326   0.9446   0.0054
  -7.250  -0.2863   0.08268   0.08046  -0.0390   0.8897   0.0054
  -7.000  -0.2736   0.07894   0.07657  -0.0432   0.8585   0.0054
  -6.750  -0.2587   0.07507   0.07259  -0.0475   0.8395   0.0054
  -6.500  -0.2508   0.07091   0.06836  -0.0489   0.8255   0.0055
  -6.000  -0.2207   0.06362   0.06091  -0.0545   0.8025   0.0057
  -5.750  -0.2017   0.05990   0.05710  -0.0580   0.7923   0.0058
  -5.500  -0.1810   0.05623   0.05331  -0.0612   0.7808   0.0059
  -5.250  -0.1588   0.05262   0.04955  -0.0642   0.7679   0.0060
  -5.000  -0.1353   0.04911   0.04588  -0.0668   0.7546   0.0062
  -4.750  -0.1106   0.04569   0.04230  -0.0691   0.7423   0.0064
  -4.500  -0.0848   0.04239   0.03883  -0.0710   0.7316   0.0066
  -4.250  -0.0583   0.03926   0.03551  -0.0725   0.7212   0.0069
  -4.000  -0.0308   0.03631   0.03234  -0.0735   0.7109   0.0072
  -3.750  -0.0009   0.03366   0.02945  -0.0740   0.7014   0.0078
  -3.500   0.0304   0.03161   0.02713  -0.0740   0.6932   0.0082
  -3.250   0.0586   0.02937   0.02464  -0.0741   0.6850   0.0083
  -2.250   0.1698   0.01959   0.01375  -0.0745   0.6554   0.0090
  -2.000   0.1967   0.01854   0.01258  -0.0750   0.6479   0.0106
  -1.750   0.2264   0.01890   0.01278  -0.0745   0.6405   0.0134
  -1.250   0.2855   0.01428   0.00750  -0.0739   0.6264   0.0078
  -1.000   0.3143   0.01315   0.00618  -0.0737   0.6183   0.0075
  -0.500   0.3711   0.01150   0.00426  -0.0733   0.6023   0.0076
  -0.250   0.3993   0.01105   0.00369  -0.0732   0.5941   0.0082
   0.000   0.4271   0.01051   0.00313  -0.0733   0.5844   0.0101
   0.250   0.4553   0.01012   0.00268  -0.0733   0.5737   0.0106
   0.500   0.4835   0.00985   0.00232  -0.0734   0.5612   0.0117
   0.750   0.5116   0.00976   0.00216  -0.0734   0.5472   0.0136
   1.000   0.5398   0.00958   0.00182  -0.0735   0.5314   0.0168
   1.250   0.5677   0.00958   0.00169  -0.0735   0.5121   0.0230
   1.500   0.5874   0.00765   0.00184  -0.0727   0.4923   0.8467
   2.000   0.6434   0.00782   0.00184  -0.0727   0.4417   1.0000
   2.250   0.6704   0.00803   0.00192  -0.0726   0.4240   1.0000
   2.500   0.6977   0.00823   0.00200  -0.0727   0.4099   1.0000
   2.750   0.7249   0.00842   0.00211  -0.0727   0.3967   1.0000
   3.000   0.7521   0.00860   0.00221  -0.0727   0.3851   1.0000
   3.250   0.7793   0.00878   0.00233  -0.0728   0.3746   1.0000
   3.500   0.8065   0.00897   0.00246  -0.0728   0.3650   1.0000
   3.750   0.8339   0.00913   0.00260  -0.0729   0.3572   1.0000
   4.000   0.8610   0.00931   0.00274  -0.0729   0.3502   1.0000
   4.250   0.8884   0.00946   0.00290  -0.0730   0.3442   1.0000
   4.500   0.9155   0.00964   0.00307  -0.0730   0.3377   1.0000
   4.750   0.9425   0.00981   0.00324  -0.0731   0.3316   1.0000
   5.000   0.9693   0.01001   0.00344  -0.0731   0.3230   1.0000
   5.250   0.9961   0.01021   0.00364  -0.0731   0.3135   1.0000
   5.500   1.0225   0.01044   0.00385  -0.0731   0.3033   1.0000
   5.750   1.0491   0.01065   0.00409  -0.0731   0.2945   1.0000
   6.000   1.0754   0.01087   0.00432  -0.0730   0.2841   1.0000
   6.250   1.1014   0.01113   0.00457  -0.0729   0.2718   1.0000
   6.500   1.1271   0.01141   0.00486  -0.0728   0.2570   1.0000
   6.750   1.1526   0.01171   0.00515  -0.0727   0.2424   1.0000
   7.000   1.1774   0.01208   0.00549  -0.0725   0.2232   1.0000
   7.250   1.1980   0.01291   0.00605  -0.0717   0.1766   1.0000
   7.500   1.2180   0.01379   0.00673  -0.0709   0.1368   1.0000
   7.750   1.2323   0.01528   0.00778  -0.0694   0.0665   1.0000
   8.000   1.2522   0.01611   0.00852  -0.0685   0.0461   1.0000
   8.250   1.2673   0.01740   0.00958  -0.0669   0.0105   1.0000
   8.500   1.2862   0.01825   0.01051  -0.0658   0.0061   1.0000
   8.750   1.3047   0.01909   0.01145  -0.0646   0.0048   1.0000
   9.000   1.3238   0.01980   0.01228  -0.0635   0.0039   1.0000
   9.250   1.3397   0.02076   0.01337  -0.0620   0.0033   1.0000
   9.500   1.3562   0.02160   0.01434  -0.0606   0.0030   1.0000
   9.750   1.3703   0.02257   0.01543  -0.0589   0.0027   1.0000
  10.000   1.3816   0.02364   0.01663  -0.0568   0.0025   1.0000
  10.250   1.3879   0.02479   0.01788  -0.0539   0.0023   1.0000
  10.500   1.3910   0.02620   0.01942  -0.0509   0.0022   1.0000
  10.750   1.3897   0.02807   0.02142  -0.0479   0.0021   1.0000
  11.000   1.3903   0.03002   0.02351  -0.0457   0.0020   1.0000
  11.250   1.3939   0.03190   0.02553  -0.0443   0.0019   1.0000
  11.500   1.3962   0.03408   0.02785  -0.0431   0.0018   1.0000
  11.750   1.3979   0.03644   0.03034  -0.0422   0.0016   1.0000
  12.000   1.3986   0.03903   0.03307  -0.0416   0.0015   1.0000
  12.250   1.3970   0.04197   0.03614  -0.0411   0.0015   1.0000
  12.500   1.3942   0.04517   0.03947  -0.0409   0.0014   1.0000
  12.750   1.3901   0.04862   0.04305  -0.0408   0.0014   1.0000
  13.000   1.3850   0.05230   0.04686  -0.0409   0.0013   1.0000
  13.250   1.3787   0.05622   0.05094  -0.0412   0.0013   1.0000
  13.500   1.3709   0.06040   0.05525  -0.0417   0.0013   1.0000
  13.750   1.3620   0.06483   0.05981  -0.0423   0.0012   1.0000
  14.000   1.3513   0.06962   0.06473  -0.0431   0.0012   1.0000
  14.250   1.3401   0.07464   0.06987  -0.0440   0.0012   1.0000
  14.500   1.3329   0.07936   0.07475  -0.0452   0.0012   1.0000
  14.750   1.3248   0.08430   0.07985  -0.0465   0.0011   1.0000
  15.000   1.3165   0.08941   0.08511  -0.0480   0.0011   1.0000
  15.250   1.3076   0.09471   0.09056  -0.0497   0.0011   1.0000
  15.500   1.2984   0.10023   0.09624  -0.0515   0.0011   1.0000
  15.750   1.2885   0.10591   0.10207  -0.0536   0.0011   1.0000
  16.000   1.2784   0.11175   0.10807  -0.0558   0.0011   1.0000
  16.250   1.2679   0.11787   0.11434  -0.0583   0.0011   1.0000
  16.500   1.2576   0.12405   0.12066  -0.0610   0.0011   1.0000
  16.750   1.2468   0.13048   0.12724  -0.0639   0.0011   1.0000
  17.000   1.2360   0.13708   0.13399  -0.0671   0.0011   1.0000
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