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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 200,000
Max Cl/Cd: 73.25 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe122-il-200000.txt
Download as CSV file: xf-goe122-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4284   0.10345   0.10004  -0.0019   1.0000   0.0292
  -8.250  -0.4255   0.10079   0.09742  -0.0065   1.0000   0.0296
  -8.000  -0.4215   0.09779   0.09447  -0.0116   1.0000   0.0298
  -7.750  -0.4102   0.09396   0.09066  -0.0184   1.0000   0.0300
  -7.500  -0.4037   0.08855   0.08528  -0.0203   1.0000   0.0303
  -7.250  -0.3979   0.08497   0.08173  -0.0154   1.0000   0.0313
  -7.000  -0.3874   0.08163   0.07841  -0.0165   1.0000   0.0321
  -6.750  -0.3752   0.07806   0.07485  -0.0195   1.0000   0.0330
  -6.500  -0.3613   0.07434   0.07113  -0.0232   1.0000   0.0341
  -6.250  -0.3454   0.07049   0.06726  -0.0274   1.0000   0.0354
  -6.000  -0.3238   0.06638   0.06310  -0.0336   1.0000   0.0374
  -5.750  -0.2904   0.06247   0.05891  -0.0430   1.0000   0.0387
  -5.500  -0.2874   0.05723   0.05372  -0.0427   1.0000   0.0395
  -5.250  -0.2855   0.05475   0.05131  -0.0403   1.0000   0.0403
  -5.000  -0.2813   0.05272   0.04931  -0.0383   1.0000   0.0414
  -4.750  -0.2647   0.05016   0.04671  -0.0392   0.9984   0.0439
  -4.500  -0.2074   0.04392   0.03991  -0.0495   0.9924   0.0509
  -4.250  -0.1761   0.04068   0.03673  -0.0527   0.9866   0.0536
  -4.000  -0.1255   0.03701   0.03242  -0.0588   0.9806   0.0635
  -3.750  -0.0927   0.03358   0.02915  -0.0620   0.9744   0.0673
  -3.500  -0.0508   0.03063   0.02587  -0.0661   0.9681   0.0796
  -3.250  -0.0124   0.02838   0.02326  -0.0689   0.9590   0.0928
  -3.000   0.0223   0.02643   0.02110  -0.0709   0.9486   0.1071
  -2.750   0.0537   0.02443   0.01901  -0.0723   0.9373   0.1227
  -2.500   0.0809   0.02289   0.01748  -0.0726   0.9242   0.1415
  -2.250   0.1056   0.02172   0.01620  -0.0721   0.9094   0.1692
  -1.500   0.1986   0.01601   0.00877  -0.0674   0.8652   0.0716
  -1.250   0.2251   0.01491   0.00737  -0.0661   0.8490   0.0662
  -1.000   0.2512   0.01426   0.00655  -0.0649   0.8321   0.0642
  -0.750   0.2771   0.01365   0.00584  -0.0639   0.8146   0.0638
  -0.500   0.3026   0.01297   0.00512  -0.0630   0.7968   0.0649
  -0.250   0.3283   0.01249   0.00462  -0.0621   0.7783   0.0677
   0.000   0.3545   0.01210   0.00418  -0.0614   0.7583   0.0687
   0.250   0.3807   0.01180   0.00381  -0.0607   0.7381   0.0703
   0.500   0.4071   0.01161   0.00351  -0.0600   0.7157   0.0731
   0.750   0.4334   0.01151   0.00324  -0.0593   0.6922   0.0777
   1.000   0.4600   0.01139   0.00304  -0.0587   0.6674   0.0923
   1.250   0.4869   0.00921   0.00297  -0.0584   0.6451   1.0000
   1.500   0.5136   0.00941   0.00294  -0.0579   0.6222   1.0000
   1.750   0.5401   0.00964   0.00295  -0.0575   0.6011   1.0000
   2.000   0.5669   0.00984   0.00299  -0.0571   0.5791   1.0000
   2.250   0.5935   0.01006   0.00305  -0.0568   0.5594   1.0000
   2.500   0.6203   0.01028   0.00314  -0.0565   0.5418   1.0000
   2.750   0.6472   0.01050   0.00326  -0.0563   0.5261   1.0000
   3.000   0.6741   0.01073   0.00339  -0.0560   0.5116   1.0000
   3.250   0.7009   0.01096   0.00354  -0.0558   0.4981   1.0000
   3.500   0.7278   0.01121   0.00373  -0.0556   0.4858   1.0000
   3.750   0.7544   0.01145   0.00391  -0.0554   0.4718   1.0000
   4.000   0.7809   0.01170   0.00410  -0.0551   0.4575   1.0000
   4.250   0.8074   0.01195   0.00433  -0.0549   0.4437   1.0000
   4.500   0.8339   0.01220   0.00457  -0.0546   0.4305   1.0000
   4.750   0.8602   0.01245   0.00481  -0.0544   0.4167   1.0000
   5.000   0.8865   0.01271   0.00507  -0.0541   0.4038   1.0000
   5.250   0.9126   0.01295   0.00534  -0.0539   0.3894   1.0000
   5.500   0.9387   0.01317   0.00560  -0.0536   0.3741   1.0000
   5.750   0.9646   0.01340   0.00586  -0.0533   0.3577   1.0000
   6.000   0.9902   0.01364   0.00612  -0.0530   0.3388   1.0000
   6.250   1.0160   0.01387   0.00642  -0.0527   0.3160   1.0000
   6.500   1.0406   0.01421   0.00669  -0.0523   0.2794   1.0000
   6.750   1.0635   0.01485   0.00710  -0.0517   0.2194   1.0000
   7.000   1.0824   0.01619   0.00799  -0.0509   0.1515   1.0000
   7.500   1.1190   0.01914   0.01040  -0.0489   0.0588   1.0000
   7.750   1.1385   0.02031   0.01167  -0.0479   0.0532   1.0000
   8.000   1.1575   0.02145   0.01295  -0.0468   0.0495   1.0000
   8.250   1.1727   0.02298   0.01454  -0.0453   0.0462   1.0000
   8.500   1.1849   0.02488   0.01651  -0.0435   0.0433   1.0000
   8.750   1.2021   0.02617   0.01791  -0.0421   0.0412   1.0000
   9.000   1.2184   0.02773   0.01954  -0.0406   0.0393   1.0000
   9.250   1.2347   0.02940   0.02126  -0.0393   0.0372   1.0000
   9.500   1.2511   0.03181   0.02362  -0.0381   0.0347   1.0000
   9.750   1.2710   0.03518   0.02714  -0.0372   0.0332   1.0000
  10.000   1.2887   0.03689   0.02910  -0.0359   0.0324   1.0000
  10.250   1.3054   0.03909   0.03154  -0.0346   0.0317   1.0000
  10.500   1.3191   0.04125   0.03398  -0.0331   0.0307   1.0000
  10.750   1.3301   0.04345   0.03644  -0.0315   0.0294   1.0000
  11.000   1.3387   0.04615   0.03940  -0.0297   0.0287   1.0000
  11.250   1.3425   0.04931   0.04291  -0.0277   0.0287   1.0000
  11.500   1.3399   0.05269   0.04664  -0.0252   0.0289   1.0000
  11.750   1.3302   0.05612   0.05038  -0.0224   0.0293   1.0000
  12.000   1.3173   0.05991   0.05446  -0.0202   0.0299   1.0000
  12.250   1.3019   0.06409   0.05890  -0.0189   0.0305   1.0000
  12.500   1.2846   0.06872   0.06378  -0.0185   0.0311   1.0000
  12.750   1.2659   0.07391   0.06918  -0.0190   0.0316   1.0000
  13.000   1.2458   0.07992   0.07538  -0.0204   0.0323   1.0000
  13.250   1.1022   0.07671   0.07236  -0.0103   0.0310   1.0000
  13.500   1.0758   0.08299   0.07881  -0.0121   0.0313   1.0000
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