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GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il)
Reynolds number: 50,000
Max Cl/Cd: 27.67 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe234-il-50000-n5.txt
Download as CSV file: xf-goe234-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 234 (MVA CA5) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1359   0.12969   0.12291  -0.0629   0.9569   0.1486
  -9.000  -0.1353   0.12803   0.12127  -0.0649   0.9487   0.1493
  -8.750  -0.1319   0.11958   0.11273  -0.0705   0.9436   0.1067
  -8.500  -0.1237   0.11480   0.10790  -0.0725   0.9375   0.0941
  -8.250  -0.1105   0.11161   0.10470  -0.0736   0.9311   0.0920
  -8.000  -0.0974   0.10806   0.10112  -0.0771   0.9264   0.0914
  -7.750  -0.0990   0.10590   0.09899  -0.0768   0.9169   0.0910
  -7.500  -0.0894   0.10257   0.09565  -0.0796   0.9112   0.0903
  -7.250  -0.0938   0.10037   0.09348  -0.0790   0.9014   0.0891
  -7.000  -0.0861   0.09631   0.08941  -0.0827   0.8950   0.0872
  -6.750  -0.0928   0.09297   0.08610  -0.0838   0.8844   0.0856
  -6.500  -0.0808   0.08801   0.08111  -0.0895   0.8786   0.0850
  -6.250  -0.0786   0.08618   0.07930  -0.0890   0.8689   0.0859
  -6.000  -0.0602   0.08275   0.07584  -0.0930   0.8633   0.0874
  -5.750  -0.0542   0.07921   0.07229  -0.0961   0.8546   0.0879
  -5.500  -0.0357   0.07298   0.06599  -0.1047   0.8478   0.0876
  -5.250   0.0372   0.05568   0.04812  -0.1405   0.8451   0.0897
  -5.000   0.1407   0.04582   0.03727  -0.1705   0.8443   0.0958
  -4.750   0.1594   0.04547   0.03694  -0.1701   0.8353   0.0979
  -4.500   0.2007   0.04430   0.03566  -0.1742   0.8308   0.1029
  -4.250   0.2471   0.04314   0.03440  -0.1789   0.8277   0.1100
  -4.000   0.2739   0.04288   0.03413  -0.1801   0.8199   0.1159
  -3.750   0.3094   0.04246   0.03375  -0.1826   0.8141   0.1252
  -3.500   0.3517   0.04201   0.03342  -0.1857   0.8105   0.1430
  -3.250   0.3714   0.04274   0.03435  -0.1840   0.8033   0.1604
  -2.750   0.4125   0.04508   0.03678  -0.1786   0.7913   0.2128
  -2.500   0.4312   0.04625   0.03781  -0.1781   0.7819   0.2428
  -2.000   0.4925   0.04792   0.03913  -0.1780   0.7725   0.2922
  -1.750   0.5014   0.04903   0.04019  -0.1758   0.7622   0.3039
  -1.500   0.5265   0.04951   0.04058  -0.1749   0.7570   0.3205
  -1.250   0.5580   0.04959   0.04055  -0.1747   0.7539   0.3391
  -1.000   0.5677   0.05058   0.04151  -0.1736   0.7431   0.3490
  -0.750   0.6039   0.05012   0.04089  -0.1758   0.7388   0.3570
  -0.500   0.6514   0.04927   0.03984  -0.1802   0.7362   0.3643
  -0.250   0.6572   0.05030   0.04088  -0.1783   0.7252   0.3683
   0.250   0.7383   0.04914   0.03946  -0.1838   0.7184   0.3835
   0.500   0.7466   0.05044   0.04075  -0.1828   0.7071   0.3885
   0.750   0.7850   0.04996   0.04017  -0.1850   0.7033   0.3959
   1.000   0.8275   0.04916   0.03927  -0.1875   0.7008   0.4030
   1.250   0.8352   0.05076   0.04086  -0.1867   0.6887   0.4066
   1.500   0.8743   0.05000   0.04004  -0.1885   0.6853   0.4114
   2.000   0.9221   0.05071   0.04070  -0.1891   0.6700   0.4178
   2.250   0.9709   0.04958   0.03945  -0.1924   0.6672   0.4213
   2.500   0.9792   0.05110   0.04098  -0.1912   0.6547   0.4238
   2.750   1.0220   0.04970   0.03956  -0.1926   0.6509   0.4271
   3.250   1.0780   0.04935   0.03918  -0.1930   0.6343   0.4305
   3.750   1.1343   0.04909   0.03887  -0.1934   0.6174   0.4357
   4.250   1.1874   0.04915   0.03894  -0.1934   0.6003   0.4404
   4.500   1.2231   0.04838   0.03815  -0.1940   0.5943   0.4422
   4.750   1.2354   0.04948   0.03933  -0.1926   0.5830   0.4433
   5.000   1.2824   0.04786   0.03766  -0.1942   0.5791   0.4460
   5.250   1.2808   0.05007   0.03997  -0.1915   0.5653   0.4476
   5.500   1.3282   0.04843   0.03828  -0.1931   0.5611   0.4518
   5.750   1.3257   0.05077   0.04072  -0.1903   0.5471   0.4533
   6.250   1.3689   0.05141   0.04142  -0.1887   0.5284   0.4572
   6.750   1.4121   0.05194   0.04202  -0.1869   0.5094   0.4608
   7.000   1.4116   0.05421   0.04439  -0.1845   0.4959   0.4624
   7.250   1.4548   0.05257   0.04271  -0.1850   0.4905   0.4670
   7.500   1.4495   0.05537   0.04562  -0.1824   0.4766   0.4688
   7.750   1.4554   0.05732   0.04764  -0.1806   0.4651   0.4710
   8.000   1.4850   0.05678   0.04711  -0.1801   0.4580   0.4741
   8.250   1.4832   0.05948   0.04991  -0.1780   0.4459   0.4756
   8.500   1.5181   0.05846   0.04889  -0.1777   0.4399   0.4787
   8.750   1.5102   0.06190   0.05244  -0.1754   0.4279   0.4798
   9.000   1.5465   0.06075   0.05126  -0.1751   0.4225   0.4838
   9.250   1.5323   0.06505   0.05569  -0.1728   0.4111   0.4852
   9.500   1.5644   0.06430   0.05498  -0.1723   0.4062   0.4896
   9.750   1.5467   0.06924   0.06008  -0.1701   0.3962   0.4908
  10.000   1.5678   0.06977   0.06068  -0.1692   0.3910   0.4948
  10.250   1.6065   0.06842   0.05934  -0.1689   0.3878   0.4998
  10.500   1.5554   0.07763   0.06879  -0.1664   0.3765   0.4986
  10.750   1.5850   0.07712   0.06833  -0.1657   0.3730   0.5025
  11.250   1.5415   0.08963   0.08115  -0.1636   0.3574   0.5035
  11.500   1.5713   0.08887   0.08050  -0.1626   0.3552   0.5075
  12.000   1.4625   0.11391   0.10580  -0.1650   0.3352   0.5040
  12.500   1.4333   0.12759   0.11970  -0.1674   0.3221   0.5056
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