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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 50,000
Max Cl/Cd: 33.62 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe133-il-50000.txt
Download as CSV file: xf-goe133-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3975   0.10657   0.09991  -0.0184   1.0000   0.1502
  -7.750  -0.3759   0.10041   0.09374  -0.0158   1.0000   0.1581
  -7.500  -0.3827   0.09902   0.09248  -0.0180   1.0000   0.1639
  -7.250  -0.3771   0.09524   0.08875  -0.0182   1.0000   0.1685
  -7.000  -0.3717   0.09234   0.08591  -0.0185   1.0000   0.1771
  -6.750  -0.3720   0.08958   0.08326  -0.0211   1.0000   0.1824
  -6.500  -0.3654   0.08656   0.08030  -0.0205   1.0000   0.1926
  -6.000  -0.3614   0.08122   0.07510  -0.0244   1.0000   0.2111
  -5.750  -0.3558   0.07849   0.07242  -0.0243   1.0000   0.2248
  -5.500  -0.3492   0.07503   0.06904  -0.0217   1.0000   0.2385
  -5.250  -0.3455   0.07233   0.06640  -0.0226   1.0000   0.2563
  -5.000  -0.3398   0.06907   0.06324  -0.0180   1.0000   0.2760
  -4.750  -0.3365   0.06653   0.06075  -0.0169   1.0000   0.3035
  -4.500   0.0149   0.04104   0.03429  -0.0221   1.0000   1.0000
  -4.250   0.0264   0.03905   0.03235  -0.0231   1.0000   1.0000
  -4.000   0.0376   0.03715   0.03050  -0.0241   1.0000   1.0000
  -3.750   0.0160   0.03733   0.03084  -0.0174   1.0000   0.9853
  -3.500  -0.0396   0.03922   0.03300  -0.0036   1.0000   0.9445
  -3.250  -0.0897   0.04037   0.03443   0.0075   1.0000   0.9039
  -3.000  -0.1392   0.04108   0.03543   0.0177   1.0000   0.8702
  -2.750  -0.1908   0.04160   0.03624   0.0279   1.0000   0.8423
  -2.500  -0.2620   0.04267   0.03763   0.0411   1.0000   0.8150
  -2.250  -0.0678   0.03442   0.02590  -0.0503   1.0000   0.1966
  -2.000  -0.0382   0.03228   0.02342  -0.0512   1.0000   0.1868
  -1.750  -0.0081   0.03069   0.02138  -0.0521   1.0000   0.1846
  -1.500   0.0223   0.02967   0.01975  -0.0527   1.0000   0.1804
  -1.250   0.0468   0.02846   0.01851  -0.0532   1.0000   0.1876
  -1.000   0.0716   0.02783   0.01760  -0.0535   1.0000   0.1909
  -0.750   0.0947   0.02753   0.01702  -0.0537   1.0000   0.1949
  -0.500   0.1152   0.02726   0.01675  -0.0539   1.0000   0.2054
  -0.250   0.1639   0.02691   0.01620  -0.0584   0.9903   0.2192
   0.000   0.2248   0.02640   0.01569  -0.0649   0.9746   0.2541
   0.250   0.2828   0.02435   0.01528  -0.0713   0.9616   0.5097
   0.500   0.3328   0.02413   0.01491  -0.0741   0.9416   1.0000
   0.750   0.3766   0.02476   0.01520  -0.0777   0.9202   1.0000
   1.000   0.4234   0.02529   0.01549  -0.0817   0.9014   1.0000
   1.250   0.4700   0.02570   0.01575  -0.0853   0.8841   1.0000
   1.500   0.5156   0.02601   0.01595  -0.0884   0.8677   1.0000
   1.750   0.5508   0.02640   0.01627  -0.0897   0.8499   1.0000
   2.000   0.5855   0.02662   0.01643  -0.0904   0.8306   1.0000
   2.250   0.6264   0.02631   0.01608  -0.0911   0.8111   1.0000
   2.500   0.6630   0.02596   0.01569  -0.0907   0.7912   1.0000
   2.750   0.6922   0.02594   0.01565  -0.0896   0.7704   1.0000
   3.000   0.7236   0.02583   0.01554  -0.0887   0.7521   1.0000
   3.250   0.7543   0.02577   0.01546  -0.0877   0.7347   1.0000
   3.500   0.7801   0.02605   0.01575  -0.0864   0.7156   1.0000
   3.750   0.8054   0.02637   0.01612  -0.0850   0.6957   1.0000
   4.000   0.8327   0.02651   0.01625  -0.0836   0.6765   1.0000
   4.250   0.8590   0.02675   0.01650  -0.0821   0.6566   1.0000
   4.500   0.8825   0.02721   0.01700  -0.0805   0.6341   1.0000
   4.750   0.9101   0.02735   0.01712  -0.0789   0.6136   1.0000
   5.000   0.9320   0.02809   0.01794  -0.0774   0.5894   1.0000
   5.250   0.9589   0.02852   0.01831  -0.0760   0.5688   1.0000
   5.500   0.9801   0.02956   0.01945  -0.0747   0.5453   1.0000
   5.750   1.0054   0.03031   0.02022  -0.0735   0.5258   1.0000
   6.000   1.0283   0.03142   0.02140  -0.0724   0.5074   1.0000
   6.250   1.0497   0.03282   0.02294  -0.0715   0.4908   1.0000
   6.500   1.0711   0.03412   0.02438  -0.0706   0.4750   1.0000
   6.750   1.0921   0.03520   0.02562  -0.0693   0.4581   1.0000
   7.000   1.1144   0.03582   0.02633  -0.0679   0.4398   1.0000
   7.250   1.1381   0.03622   0.02678  -0.0664   0.4219   1.0000
   7.500   1.1622   0.03641   0.02702  -0.0648   0.4031   1.0000
   7.750   1.1801   0.03719   0.02803  -0.0631   0.3834   1.0000
   8.000   1.2036   0.03721   0.02809  -0.0614   0.3624   1.0000
   8.250   1.2225   0.03757   0.02859  -0.0594   0.3384   1.0000
   8.500   1.2423   0.03751   0.02851  -0.0570   0.3085   1.0000
   8.750   1.2636   0.03766   0.02832  -0.0547   0.2736   1.0000
   9.000   1.2768   0.03941   0.03001  -0.0523   0.2421   1.0000
   9.250   1.2926   0.04162   0.03220  -0.0504   0.2181   1.0000
   9.500   1.3068   0.04398   0.03460  -0.0486   0.1991   1.0000
   9.750   1.3198   0.04671   0.03752  -0.0468   0.1844   1.0000
  10.000   1.3323   0.04923   0.04020  -0.0451   0.1709   1.0000
  10.250   1.3464   0.05164   0.04266  -0.0435   0.1583   1.0000
  10.500   1.3394   0.05537   0.04705  -0.0405   0.1513   1.0000
  10.750   1.3464   0.05811   0.04990  -0.0387   0.1420   1.0000
  11.000   1.3366   0.06207   0.05431  -0.0360   0.1372   1.0000
  11.250   1.3420   0.06486   0.05714  -0.0343   0.1297   1.0000
  11.500   1.3186   0.06959   0.06228  -0.0317   0.1287   1.0000
  11.750   1.2912   0.07450   0.06745  -0.0296   0.1288   1.0000
  12.000   1.2618   0.08023   0.07339  -0.0292   0.1296   1.0000
  12.250   1.2324   0.08692   0.08022  -0.0305   0.1306   1.0000
  12.500   1.2045   0.09452   0.08791  -0.0332   0.1315   1.0000
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