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GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il)
Reynolds number: 50,000
Max Cl/Cd: 37.25 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe310-il-50000.txt
Download as CSV file: xf-goe310-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 310 (MVA H.42) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3272   0.11184   0.10487  -0.0281   1.0000   0.1709
  -8.750  -0.3310   0.11025   0.10338  -0.0283   1.0000   0.1755
  -8.500  -0.3483   0.11077   0.10407  -0.0288   1.0000   0.1775
  -8.250  -0.3363   0.10558   0.09892  -0.0279   1.0000   0.1803
  -8.000  -0.3282   0.10200   0.09537  -0.0267   1.0000   0.1853
  -7.750  -0.3370   0.10068   0.09417  -0.0259   1.0000   0.1900
  -7.500  -0.3602   0.10101   0.09470  -0.0245   1.0000   0.1920
  -7.250  -0.3660   0.09844   0.09225  -0.0233   1.0000   0.1939
  -7.000  -0.3530   0.09410   0.08792  -0.0209   1.0000   0.2011
  -6.750  -0.3685   0.09336   0.08731  -0.0199   1.0000   0.2056
  -6.500  -0.3904   0.09407   0.08814  -0.0209   1.0000   0.2073
  -6.250  -0.3728   0.08797   0.08209  -0.0163   1.0000   0.2140
  -6.000  -0.3837   0.08689   0.08109  -0.0158   1.0000   0.2201
  -5.750  -0.3905   0.08483   0.07910  -0.0152   1.0000   0.2234
  -5.500  -0.3871   0.08149   0.07580  -0.0123   1.0000   0.2284
  -5.250  -0.3968   0.08160   0.07589  -0.0146   1.0000   0.2364
  -4.750  -0.3924   0.07489   0.06933  -0.0093   1.0000   0.2463
  -4.500  -0.3928   0.07289   0.06732  -0.0097   1.0000   0.2535
  -4.250  -0.3902   0.07027   0.06474  -0.0077   1.0000   0.2607
  -4.000  -0.3872   0.06804   0.06250  -0.0076   1.0000   0.2698
  -3.500  -0.3770   0.06388   0.05827  -0.0067   1.0000   0.2982
  -3.250  -0.3700   0.06163   0.05598  -0.0060   1.0000   0.3133
  -3.000  -0.3619   0.05925   0.05357  -0.0051   1.0000   0.3287
  -2.750  -0.3533   0.05681   0.05109  -0.0041   1.0000   0.3447
  -2.500  -0.3443   0.05439   0.04865  -0.0029   1.0000   0.3628
  -2.250  -0.2530   0.04719   0.03974  -0.0223   1.0000   0.1645
  -2.000  -0.2356   0.04498   0.03732  -0.0219   1.0000   0.1596
  -1.750  -0.2124   0.04252   0.03451  -0.0226   0.9989   0.1549
  -1.500  -0.1655   0.03909   0.03020  -0.0268   0.9905   0.1474
  -1.250  -0.1226   0.03697   0.02746  -0.0300   0.9822   0.1475
  -1.000  -0.0848   0.03567   0.02580  -0.0324   0.9729   0.1521
  -0.750  -0.0469   0.03495   0.02469  -0.0348   0.9637   0.1647
  -0.500  -0.0047   0.03443   0.02397  -0.0378   0.9548   0.1822
  -0.250   0.0358   0.03367   0.02293  -0.0402   0.9458   0.2243
   0.000   0.0737   0.03352   0.02288  -0.0426   0.9370   0.3162
   0.250   0.1098   0.03394   0.02322  -0.0449   0.9278   0.3720
   0.500   0.1403   0.03406   0.02332  -0.0465   0.9184   0.4093
   0.750   0.1834   0.03427   0.02348  -0.0501   0.9099   0.4410
   1.000   0.2129   0.03416   0.02357  -0.0515   0.9008   0.4883
   1.250   0.2443   0.03360   0.02377  -0.0531   0.8925   0.5669
   1.500   0.3328   0.03407   0.02452  -0.0657   0.8831   1.0000
   1.750   0.3543   0.03496   0.02513  -0.0654   0.8729   1.0000
   2.000   0.3868   0.03587   0.02577  -0.0669   0.8639   1.0000
   2.250   0.4125   0.03674   0.02645  -0.0674   0.8538   1.0000
   2.500   0.4315   0.03768   0.02726  -0.0668   0.8435   1.0000
   2.750   0.4622   0.03858   0.02804  -0.0679   0.8339   1.0000
   3.000   0.4887   0.03947   0.02886  -0.0684   0.8233   1.0000
   3.250   0.5057   0.04046   0.02980  -0.0675   0.8119   1.0000
   3.500   0.5293   0.04140   0.03071  -0.0675   0.8006   1.0000
   3.750   0.5592   0.04223   0.03153  -0.0682   0.7889   1.0000
   4.000   0.5940   0.04288   0.03222  -0.0694   0.7763   1.0000
   4.250   0.6277   0.04342   0.03281  -0.0701   0.7624   1.0000
   4.500   0.6575   0.04394   0.03338  -0.0702   0.7476   1.0000
   4.750   0.6840   0.04450   0.03401  -0.0698   0.7320   1.0000
   5.000   0.7060   0.04516   0.03478  -0.0687   0.7154   1.0000
   5.250   0.7300   0.04571   0.03543  -0.0677   0.6983   1.0000
   5.500   0.7688   0.04522   0.03508  -0.0675   0.6783   1.0000
   5.750   0.8830   0.03951   0.02979  -0.0724   0.6576   1.0000
   6.000   0.8941   0.04019   0.03058  -0.0692   0.6377   1.0000
   6.250   0.9435   0.03814   0.02878  -0.0688   0.6175   1.0000
   6.500   1.0043   0.03497   0.02582  -0.0689   0.5951   1.0000
   6.750   1.0251   0.03501   0.02606  -0.0666   0.5751   1.0000
   7.000   1.0564   0.03446   0.02570  -0.0653   0.5560   1.0000
   7.250   1.0934   0.03357   0.02499  -0.0645   0.5372   1.0000
   7.500   1.1051   0.03394   0.02556  -0.0611   0.5148   1.0000
   7.750   1.1323   0.03270   0.02447  -0.0586   0.4885   1.0000
   8.000   1.1535   0.03211   0.02405  -0.0557   0.4636   1.0000
   8.250   1.1644   0.03144   0.02347  -0.0513   0.4317   1.0000
   8.500   1.1649   0.03127   0.02336  -0.0457   0.3934   1.0000
   8.750   1.1599   0.03140   0.02324  -0.0394   0.3433   1.0000
   9.000   1.1461   0.03264   0.02400  -0.0327   0.2875   1.0000
   9.250   1.1288   0.03481   0.02563  -0.0265   0.2370   1.0000
   9.500   1.1165   0.03737   0.02766  -0.0219   0.1985   1.0000
   9.750   1.1122   0.03985   0.02981  -0.0184   0.1698   1.0000
  10.000   1.1166   0.04212   0.03201  -0.0158   0.1477   1.0000
  10.250   1.1266   0.04420   0.03391  -0.0136   0.1308   1.0000
  10.500   1.1604   0.04634   0.03590  -0.0129   0.1150   1.0000
  10.750   1.1991   0.04898   0.03851  -0.0134   0.1027   1.0000
  11.000   1.2307   0.05252   0.04258  -0.0133   0.0981   1.0000
  11.250   1.2539   0.05618   0.04657  -0.0129   0.0944   1.0000
  11.500   1.2775   0.06052   0.05101  -0.0132   0.0906   1.0000
  11.750   1.2699   0.06375   0.05464  -0.0097   0.0900   1.0000
  12.000   1.2589   0.06721   0.05845  -0.0065   0.0897   1.0000
  12.250   1.2476   0.07099   0.06253  -0.0039   0.0899   1.0000
  12.500   1.2340   0.07510   0.06691  -0.0018   0.0902   1.0000
  12.750   1.2197   0.07946   0.07150  -0.0003   0.0906   1.0000
  13.000   1.2026   0.08415   0.07643   0.0007   0.0911   1.0000
  13.250   1.1521   0.08923   0.08185   0.0001   0.0924   1.0000
  13.500   1.0707   0.10133   0.09426  -0.0068   0.0991   1.0000
  13.750   1.0448   0.10972   0.10271  -0.0107   0.1013   1.0000
  14.000   1.0260   0.11783   0.11084  -0.0142   0.1026   1.0000
  14.250   0.9484   0.14158   0.13444  -0.0307   0.1147   1.0000
  14.500   0.9151   0.15591   0.14857  -0.0399   0.1251   1.0000
  14.750   0.9016   0.16542   0.15800  -0.0453   0.1359   1.0000
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