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GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il)
Reynolds number: 50,000
Max Cl/Cd: 38.66 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe117-il-50000-n5.txt
Download as CSV file: xf-goe117-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 117 (MVA MK.4) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3391   0.10842   0.10182  -0.0396   1.0000   0.1132
  -8.500  -0.3483   0.10666   0.10020  -0.0401   1.0000   0.1136
  -8.000  -0.3621   0.09579   0.08952  -0.0429   1.0000   0.0592
  -7.750  -0.3661   0.09298   0.08681  -0.0419   1.0000   0.0589
  -7.500  -0.3683   0.09025   0.08416  -0.0405   1.0000   0.0584
  -7.250  -0.3728   0.08765   0.08166  -0.0392   1.0000   0.0578
  -7.000  -0.3784   0.08511   0.07920  -0.0381   1.0000   0.0570
  -6.750  -0.3842   0.08243   0.07660  -0.0375   1.0000   0.0562
  -6.500  -0.3891   0.07962   0.07386  -0.0372   1.0000   0.0554
  -6.250  -0.3924   0.07649   0.07079  -0.0376   1.0000   0.0547
  -6.000  -0.3805   0.07158   0.06583  -0.0424   0.9958   0.0537
  -5.750  -0.3498   0.06456   0.05864  -0.0523   0.9864   0.0543
  -5.500  -0.3167   0.05674   0.05051  -0.0625   0.9769   0.0560
  -5.250  -0.2834   0.04866   0.04187  -0.0714   0.9674   0.0571
  -5.000  -0.2498   0.04191   0.03434  -0.0777   0.9582   0.0579
  -4.750  -0.2156   0.03753   0.02936  -0.0819   0.9500   0.0619
  -4.500  -0.1809   0.03474   0.02611  -0.0847   0.9413   0.0676
  -4.250  -0.1460   0.03148   0.02199  -0.0870   0.9326   0.0708
  -4.000  -0.1077   0.02954   0.01968  -0.0897   0.9254   0.0793
  -3.750  -0.0742   0.02782   0.01749  -0.0909   0.9154   0.0845
  -3.500  -0.0365   0.02630   0.01561  -0.0927   0.9075   0.0893
  -3.250   0.0006   0.02525   0.01434  -0.0944   0.8990   0.0972
  -3.000   0.0362   0.02442   0.01337  -0.0958   0.8895   0.1105
  -2.750   0.0772   0.02363   0.01254  -0.0982   0.8824   0.1562
  -2.500   0.1083   0.02333   0.01234  -0.0989   0.8710   0.2194
  -2.250   0.1393   0.02339   0.01228  -0.0996   0.8600   0.2725
  -2.000   0.1700   0.02334   0.01220  -0.1002   0.8501   0.3284
  -1.750   0.2038   0.02294   0.01166  -0.1012   0.8410   0.3574
  -1.500   0.2332   0.02263   0.01124  -0.1015   0.8300   0.3759
  -1.250   0.2633   0.02232   0.01088  -0.1018   0.8200   0.3999
  -1.000   0.2955   0.02191   0.01049  -0.1025   0.8118   0.4320
  -0.750   0.3208   0.02164   0.01034  -0.1021   0.8008   0.4747
  -0.500   0.3454   0.02104   0.01019  -0.1014   0.7914   0.5702
  -0.250   0.3921   0.02024   0.00984  -0.1043   0.7841   1.0000
   0.000   0.4178   0.02052   0.00986  -0.1040   0.7739   1.0000
   0.250   0.4473   0.02068   0.00979  -0.1043   0.7661   1.0000
   0.500   0.4728   0.02097   0.00990  -0.1039   0.7567   1.0000
   0.750   0.4985   0.02127   0.01004  -0.1037   0.7481   1.0000
   1.000   0.5267   0.02148   0.01012  -0.1037   0.7408   1.0000
   1.250   0.5503   0.02186   0.01042  -0.1032   0.7320   1.0000
   1.500   0.5793   0.02205   0.01052  -0.1033   0.7257   1.0000
   1.750   0.6016   0.02252   0.01094  -0.1026   0.7172   1.0000
   2.000   0.6307   0.02271   0.01110  -0.1027   0.7112   1.0000
   2.250   0.6523   0.02322   0.01162  -0.1019   0.7028   1.0000
   2.500   0.6812   0.02344   0.01182  -0.1020   0.6972   1.0000
   2.750   0.7024   0.02400   0.01242  -0.1012   0.6889   1.0000
   3.000   0.7309   0.02424   0.01272  -0.1012   0.6832   1.0000
   3.250   0.7520   0.02484   0.01340  -0.1003   0.6752   1.0000
   3.500   0.7800   0.02512   0.01375  -0.1002   0.6693   1.0000
   3.750   0.8009   0.02575   0.01453  -0.0994   0.6615   1.0000
   4.000   0.8282   0.02608   0.01498  -0.0992   0.6554   1.0000
   4.250   0.8489   0.02676   0.01581  -0.0983   0.6477   1.0000
   4.500   0.8752   0.02718   0.01639  -0.0980   0.6414   1.0000
   4.750   0.8959   0.02791   0.01736  -0.0971   0.6340   1.0000
   5.000   0.9205   0.02846   0.01812  -0.0966   0.6275   1.0000
   5.250   0.9417   0.02922   0.01913  -0.0958   0.6206   1.0000
   5.500   0.9728   0.02900   0.01914  -0.0951   0.6094   1.0000
   5.750   0.9997   0.02694   0.01708  -0.0910   0.5659   1.0000
   6.000   1.0105   0.02644   0.01666  -0.0866   0.5264   1.0000
   6.250   1.0190   0.02636   0.01674  -0.0823   0.4859   1.0000
   6.500   1.0156   0.02652   0.01672  -0.0762   0.3804   1.0000
   6.750   0.9914   0.02944   0.01771  -0.0692   0.1409   1.0000
   7.000   0.9778   0.03246   0.02025  -0.0647   0.1049   1.0000
   7.250   0.9728   0.03493   0.02272  -0.0614   0.0899   1.0000
   7.500   0.9696   0.03734   0.02519  -0.0587   0.0783   1.0000
   7.750   0.9668   0.03982   0.02776  -0.0564   0.0710   1.0000
   8.000   0.9655   0.04229   0.03039  -0.0544   0.0660   1.0000
   8.250   0.9632   0.04496   0.03319  -0.0526   0.0621   1.0000
   8.500   0.9652   0.04732   0.03569  -0.0509   0.0578   1.0000
   8.750   0.9707   0.04942   0.03792  -0.0493   0.0527   1.0000
   9.000   0.9806   0.05122   0.03973  -0.0473   0.0491   1.0000
   9.250   1.0233   0.05134   0.03999  -0.0445   0.0441   1.0000
   9.500   1.1488   0.05405   0.04269  -0.0496   0.0363   1.0000
   9.750   1.1708   0.05676   0.04602  -0.0485   0.0347   1.0000
  10.000   1.1855   0.05972   0.04943  -0.0470   0.0330   1.0000
  10.250   1.1958   0.06296   0.05306  -0.0453   0.0321   1.0000
  10.500   1.2013   0.06636   0.05682  -0.0432   0.0318   1.0000
  10.750   1.2007   0.06980   0.06061  -0.0409   0.0317   1.0000
  11.000   1.1956   0.07322   0.06434  -0.0386   0.0317   1.0000
  11.250   1.1865   0.07676   0.06818  -0.0366   0.0317   1.0000
  11.500   1.1747   0.08045   0.07215  -0.0350   0.0318   1.0000
  11.750   1.1606   0.08442   0.07638  -0.0339   0.0319   1.0000
  12.000   1.1449   0.08868   0.08089  -0.0335   0.0321   1.0000
  12.250   1.1275   0.09330   0.08573  -0.0338   0.0322   1.0000
  12.500   1.1092   0.09831   0.09095  -0.0348   0.0324   1.0000
  12.750   1.0900   0.10379   0.09663  -0.0366   0.0326   1.0000
  13.000   1.0709   0.10972   0.10272  -0.0391   0.0329   1.0000
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