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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 50,000
Max Cl/Cd: 37.59 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe122-il-50000.txt
Download as CSV file: xf-goe122-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 122 (MVA H.2) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4544   0.11841   0.11180  -0.0044   1.0000   0.1348
  -8.500  -0.4286   0.11070   0.10405  -0.0008   1.0000   0.1438
  -8.250  -0.4338   0.10956   0.10302  -0.0043   1.0000   0.1488
  -8.000  -0.4216   0.10460   0.09809  -0.0038   1.0000   0.1539
  -7.750  -0.4175   0.10189   0.09544  -0.0051   1.0000   0.1619
  -7.500  -0.4209   0.09995   0.09363  -0.0099   1.0000   0.1657
  -7.250  -0.4065   0.09548   0.08914  -0.0077   1.0000   0.1763
  -6.750  -0.3976   0.09052   0.08430  -0.0164   1.0000   0.1943
  -6.500  -0.3846   0.08589   0.07974  -0.0131   1.0000   0.2069
  -6.250  -0.3756   0.08250   0.07640  -0.0135   1.0000   0.2208
  -6.000  -0.3680   0.07970   0.07366  -0.0157   1.0000   0.2376
  -5.750  -0.3605   0.07683   0.07085  -0.0179   1.0000   0.2549
  -5.500  -0.3505   0.07302   0.06711  -0.0150   1.0000   0.2725
  -5.250  -0.3421   0.07012   0.06428  -0.0140   1.0000   0.2945
  -5.000  -0.3358   0.06714   0.06136  -0.0129   1.0000   0.3177
  -4.750  -0.3311   0.06446   0.05878  -0.0108   1.0000   0.3465
  -4.500  -0.3275   0.06182   0.05624  -0.0069   1.0000   0.3791
  -4.250  -0.0197   0.03956   0.03309  -0.0099   1.0000   0.9965
  -4.000  -0.0745   0.04187   0.03565   0.0038   1.0000   0.9565
  -3.750  -0.0451   0.03876   0.03253  -0.0011   1.0000   0.9694
  -3.500  -0.0758   0.03896   0.03293   0.0063   1.0000   0.9331
  -3.250  -0.1147   0.03943   0.03363   0.0143   1.0000   0.8976
  -3.000  -0.1512   0.03941   0.03389   0.0209   1.0000   0.8638
  -2.750  -0.1961   0.03947   0.03424   0.0294   1.0000   0.8397
  -2.500  -0.2578   0.04004   0.03510   0.0414   1.0000   0.8234
  -2.250  -0.0878   0.03562   0.02768  -0.0438   1.0000   0.2247
  -2.000  -0.0554   0.03303   0.02459  -0.0454   1.0000   0.1910
  -1.750  -0.0256   0.03115   0.02223  -0.0463   1.0000   0.1730
  -1.500   0.0035   0.02980   0.02033  -0.0470   1.0000   0.1616
  -1.250   0.0297   0.02874   0.01899  -0.0476   1.0000   0.1595
  -1.000   0.0547   0.02800   0.01798  -0.0480   1.0000   0.1593
  -0.750   0.0786   0.02745   0.01720  -0.0483   1.0000   0.1574
  -0.500   0.1356   0.02660   0.01597  -0.0539   0.9869   0.1568
  -0.250   0.2020   0.02591   0.01497  -0.0608   0.9705   0.1626
   0.000   0.2598   0.02529   0.01436  -0.0665   0.9504   0.1809
   0.250   0.3188   0.02457   0.01387  -0.0723   0.9306   0.2171
   0.500   0.3784   0.02226   0.01322  -0.0769   0.9133   1.0000
   0.750   0.4256   0.02264   0.01313  -0.0800   0.8898   1.0000
   1.000   0.4725   0.02289   0.01311  -0.0828   0.8690   1.0000
   1.250   0.5052   0.02331   0.01337  -0.0833   0.8454   1.0000
   1.500   0.5399   0.02359   0.01352  -0.0837   0.8256   1.0000
   1.750   0.5681   0.02402   0.01384  -0.0832   0.8053   1.0000
   2.000   0.5949   0.02448   0.01422  -0.0826   0.7861   1.0000
   2.250   0.6221   0.02490   0.01458  -0.0819   0.7690   1.0000
   2.500   0.6486   0.02534   0.01499  -0.0811   0.7530   1.0000
   2.750   0.6742   0.02586   0.01547  -0.0802   0.7377   1.0000
   3.000   0.6993   0.02644   0.01604  -0.0794   0.7229   1.0000
   3.250   0.7240   0.02700   0.01661  -0.0785   0.7081   1.0000
   3.500   0.7486   0.02750   0.01714  -0.0773   0.6931   1.0000
   3.750   0.7736   0.02774   0.01737  -0.0756   0.6771   1.0000
   4.000   0.7962   0.02819   0.01785  -0.0740   0.6586   1.0000
   4.250   0.8193   0.02859   0.01828  -0.0724   0.6404   1.0000
   4.500   0.8430   0.02909   0.01887  -0.0710   0.6244   1.0000
   4.750   0.8667   0.02977   0.01964  -0.0700   0.6094   1.0000
   5.000   0.8901   0.03050   0.02046  -0.0689   0.5942   1.0000
   5.250   0.9134   0.03125   0.02133  -0.0678   0.5788   1.0000
   5.500   0.9368   0.03196   0.02220  -0.0665   0.5629   1.0000
   5.750   0.9605   0.03263   0.02299  -0.0652   0.5467   1.0000
   6.000   0.9843   0.03333   0.02382  -0.0639   0.5306   1.0000
   6.250   1.0085   0.03380   0.02439  -0.0623   0.5131   1.0000
   6.500   1.0305   0.03378   0.02451  -0.0600   0.4887   1.0000
   6.750   1.0541   0.03334   0.02410  -0.0576   0.4643   1.0000
   7.000   1.0790   0.03311   0.02392  -0.0555   0.4432   1.0000
   7.250   1.1014   0.03333   0.02428  -0.0538   0.4222   1.0000
   7.500   1.1259   0.03245   0.02340  -0.0514   0.3963   1.0000
   7.750   1.1443   0.03184   0.02297  -0.0489   0.3643   1.0000
   8.000   1.1594   0.03092   0.02216  -0.0458   0.3216   1.0000
   8.250   1.1633   0.03095   0.02208  -0.0419   0.2457   1.0000
   8.500   1.1629   0.03348   0.02371  -0.0387   0.1812   1.0000
   8.750   1.1727   0.03634   0.02626  -0.0364   0.1527   1.0000
   9.000   1.1870   0.03873   0.02868  -0.0346   0.1345   1.0000
   9.250   1.2039   0.04103   0.03100  -0.0330   0.1222   1.0000
   9.500   1.2260   0.04346   0.03332  -0.0318   0.1137   1.0000
   9.750   1.2424   0.04608   0.03632  -0.0304   0.1064   1.0000
  10.000   1.2627   0.04901   0.03926  -0.0294   0.1008   1.0000
  10.250   1.2758   0.05282   0.04363  -0.0280   0.0986   1.0000
  10.500   1.2828   0.05680   0.04807  -0.0264   0.0966   1.0000
  10.750   1.2855   0.06070   0.05233  -0.0249   0.0946   1.0000
  11.000   1.2923   0.06433   0.05612  -0.0237   0.0919   1.0000
  11.250   1.2959   0.06884   0.06081  -0.0226   0.0904   1.0000
  11.500   1.2767   0.07316   0.06555  -0.0208   0.0909   1.0000
  11.750   1.2121   0.07975   0.07271  -0.0209   0.0953   1.0000
  12.000   1.1766   0.08720   0.08039  -0.0239   0.0979   1.0000
  12.250   1.1476   0.09519   0.08850  -0.0280   0.0998   1.0000
  12.500   1.1244   0.10339   0.09672  -0.0322   0.1012   1.0000
  12.750   0.9999   0.13851   0.13157  -0.0595   0.1218   1.0000
  13.000   0.9919   0.14619   0.13921  -0.0629   0.1241   1.0000
  13.250   0.9897   0.15271   0.14571  -0.0653   0.1255   1.0000
  13.500   0.9937   0.15835   0.15136  -0.0665   0.1268   1.0000
  13.750   0.7162   0.16352   0.15669  -0.0593   0.2507   1.0000
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