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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 50,000
Max Cl/Cd: 36.1 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe147-il-50000-n5.txt
Download as CSV file: xf-goe147-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 147 (MVA H.6) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4452   0.10188   0.09540  -0.0002   1.0000   0.0506
  -7.750  -0.4377   0.09815   0.09171  -0.0011   1.0000   0.0500
  -7.500  -0.4312   0.09437   0.08799  -0.0034   1.0000   0.0497
  -7.250  -0.4232   0.09037   0.08405  -0.0065   1.0000   0.0496
  -7.000  -0.4138   0.08621   0.07992  -0.0101   1.0000   0.0495
  -6.750  -0.4027   0.08190   0.07564  -0.0139   1.0000   0.0494
  -6.500  -0.3900   0.07745   0.07121  -0.0177   1.0000   0.0492
  -6.250  -0.3755   0.07288   0.06664  -0.0217   1.0000   0.0487
  -6.000  -0.3589   0.06810   0.06183  -0.0259   1.0000   0.0483
  -5.750  -0.3400   0.06307   0.05674  -0.0304   1.0000   0.0481
  -5.500  -0.3185   0.05771   0.05126  -0.0351   1.0000   0.0482
  -5.250  -0.2932   0.05158   0.04492  -0.0406   1.0000   0.0495
  -5.000  -0.2645   0.04442   0.03741  -0.0464   1.0000   0.0514
  -4.750  -0.2419   0.04273   0.03561  -0.0469   1.0000   0.0545
  -4.500  -0.2133   0.03794   0.03045  -0.0498   1.0000   0.0569
  -4.250  -0.1803   0.03152   0.02319  -0.0535   1.0000   0.0628
  -4.000  -0.1558   0.03102   0.02266  -0.0532   1.0000   0.0708
  -3.750  -0.1277   0.02856   0.01980  -0.0538   1.0000   0.0805
  -3.500  -0.1002   0.02692   0.01773  -0.0541   1.0000   0.1007
  -3.250  -0.0744   0.02576   0.01620  -0.0539   1.0000   0.1264
  -3.000  -0.0522   0.02557   0.01604  -0.0532   1.0000   0.1459
  -2.750  -0.0306   0.02566   0.01605  -0.0526   1.0000   0.1703
  -2.500  -0.0080   0.02510   0.01528  -0.0522   1.0000   0.1831
  -2.250   0.0132   0.02453   0.01458  -0.0516   1.0000   0.1897
  -2.000   0.0531   0.02376   0.01340  -0.0544   0.9870   0.1959
  -1.750   0.1001   0.02292   0.01235  -0.0584   0.9664   0.1994
  -1.500   0.1472   0.02223   0.01142  -0.0620   0.9407   0.2047
  -1.250   0.1923   0.02165   0.01057  -0.0647   0.9114   0.2113
  -1.000   0.2329   0.02112   0.00985  -0.0664   0.8809   0.2158
  -0.750   0.2681   0.02072   0.00925  -0.0670   0.8511   0.2203
  -0.500   0.2988   0.02043   0.00877  -0.0666   0.8225   0.2254
  -0.250   0.3266   0.02017   0.00840  -0.0658   0.7947   0.2313
   0.000   0.3532   0.02000   0.00809  -0.0648   0.7680   0.2395
   0.250   0.3788   0.01983   0.00785  -0.0637   0.7427   0.2518
   0.500   0.4043   0.01967   0.00765  -0.0626   0.7182   0.2687
   0.750   0.4297   0.01945   0.00749  -0.0617   0.6939   0.2926
   1.250   0.4776   0.01766   0.00718  -0.0589   0.6480   1.0000
   1.500   0.5035   0.01795   0.00714  -0.0579   0.6257   1.0000
   1.750   0.5294   0.01826   0.00720  -0.0570   0.6022   1.0000
   2.000   0.5552   0.01858   0.00731  -0.0562   0.5795   1.0000
   2.250   0.5810   0.01893   0.00748  -0.0555   0.5567   1.0000
   2.500   0.6068   0.01929   0.00768  -0.0548   0.5342   1.0000
   2.750   0.6326   0.01968   0.00795  -0.0541   0.5118   1.0000
   3.000   0.6584   0.02008   0.00822  -0.0535   0.4907   1.0000
   3.250   0.6846   0.02050   0.00857  -0.0531   0.4691   1.0000
   3.500   0.7106   0.02093   0.00892  -0.0526   0.4498   1.0000
   3.750   0.7365   0.02138   0.00931  -0.0521   0.4296   1.0000
   4.000   0.7620   0.02181   0.00967  -0.0516   0.4095   1.0000
   4.250   0.7872   0.02226   0.01003  -0.0510   0.3912   1.0000
   4.500   0.8124   0.02277   0.01047  -0.0505   0.3733   1.0000
   4.750   0.8376   0.02332   0.01099  -0.0500   0.3571   1.0000
   5.000   0.8627   0.02393   0.01161  -0.0496   0.3429   1.0000
   5.250   0.8878   0.02459   0.01225  -0.0491   0.3302   1.0000
   5.500   0.9128   0.02529   0.01297  -0.0487   0.3182   1.0000
   5.750   0.9378   0.02605   0.01384  -0.0483   0.3063   1.0000
   6.000   0.9627   0.02687   0.01480  -0.0479   0.2960   1.0000
   6.500   1.0122   0.02867   0.01686  -0.0471   0.2785   1.0000
   6.750   1.0369   0.02961   0.01786  -0.0467   0.2717   1.0000
   7.000   1.0610   0.03074   0.01934  -0.0463   0.2641   1.0000
   7.250   1.0856   0.03175   0.02044  -0.0459   0.2587   1.0000
   7.500   1.1086   0.03309   0.02213  -0.0455   0.2524   1.0000
   7.750   1.1319   0.03431   0.02361  -0.0451   0.2470   1.0000
   8.000   1.1563   0.03540   0.02482  -0.0446   0.2430   1.0000
   8.250   1.1765   0.03716   0.02716  -0.0442   0.2378   1.0000
   8.500   1.1975   0.03881   0.02921  -0.0438   0.2340   1.0000
   8.750   1.2203   0.03991   0.03056  -0.0431   0.2296   1.0000
   9.000   1.2360   0.03924   0.03008  -0.0417   0.2095   1.0000
   9.250   1.2490   0.03829   0.02923  -0.0402   0.1852   1.0000
   9.500   1.2610   0.03883   0.03020  -0.0392   0.1639   1.0000
   9.750   1.2715   0.03961   0.03119  -0.0382   0.1345   1.0000
  10.250   1.2684   0.04524   0.03644  -0.0363   0.0603   1.0000
  10.500   1.2556   0.04915   0.04027  -0.0354   0.0551   1.0000
  10.750   1.2434   0.05349   0.04478  -0.0358   0.0524   1.0000
  11.000   1.2303   0.05864   0.05012  -0.0376   0.0507   1.0000
  11.250   1.2165   0.06443   0.05611  -0.0403   0.0495   1.0000
  11.500   1.2023   0.07058   0.06243  -0.0433   0.0486   1.0000
  11.750   1.1880   0.07685   0.06885  -0.0462   0.0478   1.0000
  12.000   1.1741   0.08307   0.07518  -0.0489   0.0470   1.0000
  12.250   1.1612   0.08911   0.08131  -0.0514   0.0461   1.0000
  12.500   1.1494   0.09488   0.08712  -0.0536   0.0451   1.0000
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