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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 500,000
Max Cl/Cd: 99.19 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe133-il-500000.txt
Download as CSV file: xf-goe133-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 133 (MVA H.11) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3865   0.09226   0.09005  -0.0226   1.0000   0.0198
  -8.000  -0.3840   0.08890   0.08673  -0.0247   1.0000   0.0199
  -7.750  -0.3840   0.08451   0.08238  -0.0257   1.0000   0.0202
  -7.500  -0.3779   0.08187   0.07976  -0.0252   1.0000   0.0204
  -7.250  -0.3743   0.07934   0.07726  -0.0254   1.0000   0.0206
  -7.000  -0.3734   0.07691   0.07486  -0.0255   1.0000   0.0209
  -6.750  -0.3744   0.07454   0.07251  -0.0254   1.0000   0.0211
  -6.500  -0.3696   0.07167   0.06965  -0.0267   0.9995   0.0215
  -6.250  -0.3381   0.06654   0.06447  -0.0352   0.9963   0.0226
  -6.000  -0.2852   0.05755   0.05527  -0.0523   0.9917   0.0249
  -5.750  -0.2529   0.04909   0.04663  -0.0611   0.9876   0.0254
  -5.500  -0.2246   0.04621   0.04372  -0.0644   0.9853   0.0260
  -5.250  -0.1908   0.04319   0.04062  -0.0686   0.9833   0.0270
  -5.000  -0.1570   0.03949   0.03677  -0.0725   0.9784   0.0292
  -4.750  -0.1154   0.02680   0.02331  -0.0794   0.9742   0.0234
  -4.500  -0.0811   0.01530   0.01033  -0.0822   0.9711   0.0240
  -4.250  -0.0517   0.01376   0.00848  -0.0825   0.9646   0.0261
  -4.000  -0.0195   0.01365   0.00837  -0.0833   0.9590   0.0279
  -3.750   0.0099   0.01290   0.00747  -0.0833   0.9520   0.0301
  -3.500   0.0378   0.01185   0.00622  -0.0830   0.9438   0.0327
  -3.250   0.0646   0.01181   0.00621  -0.0826   0.9336   0.0353
  -3.000   0.0916   0.01158   0.00590  -0.0820   0.9233   0.0384
  -2.750   0.1177   0.01074   0.00494  -0.0813   0.9120   0.0415
  -2.500   0.1440   0.01057   0.00476  -0.0807   0.8984   0.0449
  -2.250   0.1705   0.01032   0.00444  -0.0801   0.8837   0.0481
  -2.000   0.1971   0.01025   0.00427  -0.0794   0.8654   0.0503
  -1.750   0.2226   0.00940   0.00334  -0.0787   0.8427   0.0544
  -1.500   0.2487   0.00922   0.00305  -0.0780   0.8149   0.0578
  -1.250   0.2750   0.00908   0.00276  -0.0774   0.7858   0.0606
  -1.000   0.3014   0.00901   0.00253  -0.0768   0.7560   0.0626
  -0.750   0.3278   0.00874   0.00213  -0.0763   0.7274   0.0671
  -0.500   0.3546   0.00870   0.00196  -0.0759   0.6983   0.0711
  -0.250   0.3815   0.00870   0.00183  -0.0756   0.6690   0.0753
   0.000   0.4084   0.00867   0.00170  -0.0753   0.6381   0.0829
   0.250   0.4353   0.00869   0.00163  -0.0750   0.6064   0.0980
   0.500   0.4620   0.00845   0.00162  -0.0749   0.5781   0.2233
   0.750   0.4853   0.00667   0.00171  -0.0741   0.5555   1.0000
   1.000   0.5125   0.00685   0.00173  -0.0739   0.5378   1.0000
   1.250   0.5398   0.00701   0.00176  -0.0737   0.5239   1.0000
   1.500   0.5673   0.00715   0.00181  -0.0735   0.5115   1.0000
   1.750   0.5949   0.00729   0.00187  -0.0734   0.5003   1.0000
   2.000   0.6224   0.00744   0.00193  -0.0733   0.4901   1.0000
   2.250   0.6498   0.00759   0.00201  -0.0731   0.4800   1.0000
   2.500   0.6775   0.00771   0.00209  -0.0730   0.4702   1.0000
   2.750   0.7049   0.00786   0.00219  -0.0729   0.4608   1.0000
   3.000   0.7323   0.00801   0.00228  -0.0728   0.4502   1.0000
   3.250   0.7597   0.00814   0.00238  -0.0726   0.4379   1.0000
   3.500   0.7869   0.00829   0.00248  -0.0725   0.4246   1.0000
   3.750   0.8141   0.00845   0.00260  -0.0724   0.4109   1.0000
   4.000   0.8413   0.00861   0.00273  -0.0722   0.3968   1.0000
   4.250   0.8682   0.00879   0.00286  -0.0720   0.3797   1.0000
   4.500   0.8947   0.00902   0.00302  -0.0718   0.3562   1.0000
   4.750   0.9206   0.00933   0.00319  -0.0716   0.3225   1.0000
   5.000   0.9455   0.00979   0.00343  -0.0712   0.2808   1.0000
   5.250   0.9703   0.01026   0.00373  -0.0708   0.2518   1.0000
   5.500   0.9957   0.01065   0.00405  -0.0705   0.2346   1.0000
   5.750   1.0214   0.01098   0.00434  -0.0702   0.2232   1.0000
   6.000   1.0470   0.01131   0.00464  -0.0699   0.2147   1.0000
   6.250   1.0731   0.01158   0.00493  -0.0697   0.2073   1.0000
   6.500   1.0986   0.01190   0.00525  -0.0694   0.1996   1.0000
   6.750   1.1244   0.01217   0.00554  -0.0691   0.1915   1.0000
   7.000   1.1500   0.01247   0.00585  -0.0688   0.1838   1.0000
   7.250   1.1752   0.01280   0.00619  -0.0685   0.1740   1.0000
   7.500   1.2004   0.01313   0.00651  -0.0681   0.1599   1.0000
   7.750   1.2242   0.01363   0.00686  -0.0677   0.1226   1.0000
   8.000   1.2428   0.01477   0.00767  -0.0666   0.0816   1.0000
   8.250   1.2642   0.01552   0.00843  -0.0658   0.0728   1.0000
   8.500   1.2870   0.01606   0.00904  -0.0651   0.0671   1.0000
   8.750   1.3091   0.01667   0.00967  -0.0644   0.0617   1.0000
   9.000   1.3303   0.01735   0.01039  -0.0635   0.0567   1.0000
   9.250   1.3533   0.01778   0.01088  -0.0630   0.0526   1.0000
   9.500   1.3727   0.01859   0.01170  -0.0619   0.0473   1.0000
   9.750   1.3958   0.01897   0.01216  -0.0613   0.0438   1.0000
  10.000   1.4150   0.01973   0.01289  -0.0603   0.0382   1.0000
  10.250   1.4362   0.02024   0.01348  -0.0595   0.0334   1.0000
  10.500   1.4530   0.02117   0.01442  -0.0581   0.0282   1.0000
  10.750   1.4696   0.02204   0.01531  -0.0568   0.0242   1.0000
  11.000   1.4836   0.02309   0.01644  -0.0550   0.0214   1.0000
  11.250   1.4983   0.02398   0.01738  -0.0534   0.0194   1.0000
  11.500   1.5017   0.02551   0.01897  -0.0503   0.0176   1.0000
  11.750   1.5121   0.02645   0.02005  -0.0481   0.0167   1.0000
  12.000   1.5192   0.02765   0.02135  -0.0458   0.0158   1.0000
  12.250   1.5246   0.02903   0.02283  -0.0435   0.0150   1.0000
  12.500   1.5261   0.03080   0.02469  -0.0413   0.0144   1.0000
  12.750   1.5210   0.03328   0.02728  -0.0390   0.0138   1.0000
  13.000   1.5131   0.03629   0.03043  -0.0372   0.0134   1.0000
  13.250   1.5146   0.03863   0.03291  -0.0363   0.0131   1.0000
  13.500   1.5138   0.04141   0.03584  -0.0358   0.0128   1.0000
  13.750   1.5119   0.04450   0.03907  -0.0357   0.0125   1.0000
  14.000   1.5087   0.04791   0.04263  -0.0359   0.0121   1.0000
  14.250   1.5047   0.05159   0.04645  -0.0365   0.0118   1.0000
  14.500   1.4996   0.05556   0.05054  -0.0373   0.0116   1.0000
  14.750   1.4930   0.05985   0.05495  -0.0384   0.0113   1.0000
  15.000   1.4853   0.06440   0.05961  -0.0398   0.0111   1.0000
  15.250   1.4756   0.06926   0.06459  -0.0412   0.0109   1.0000
  15.500   1.4647   0.07438   0.06983  -0.0428   0.0107   1.0000
  15.750   1.4521   0.07978   0.07534  -0.0445   0.0106   1.0000
  16.000   1.4387   0.08536   0.08104  -0.0462   0.0104   1.0000
  16.250   1.4241   0.09118   0.08698  -0.0480   0.0103   1.0000
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