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GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il)
Reynolds number: 200,000
Max Cl/Cd: 85.48 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe226-il-200000.txt
Download as CSV file: xf-goe226-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 226 (MVA H.36) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0539   0.09606   0.09219  -0.1048   0.9158   0.0728
  -9.000   0.0452   0.09458   0.09071  -0.1091   0.9059   0.0765
  -8.750   0.0445   0.09139   0.08752  -0.1113   0.8971   0.0773
  -8.500   0.0640   0.08862   0.08473  -0.1087   0.8914   0.0782
  -8.250   0.0774   0.08647   0.08253  -0.1075   0.8861   0.0795
  -8.000   0.0877   0.08446   0.08053  -0.1078   0.8772   0.0812
  -7.750   0.0951   0.08229   0.07832  -0.1084   0.8703   0.0836
  -7.500   0.0782   0.07981   0.07588  -0.1204   0.8569   0.0873
  -7.250   0.0923   0.07674   0.07277  -0.1160   0.8529   0.0880
  -7.000   0.1091   0.07479   0.07080  -0.1135   0.8478   0.0891
  -6.750   0.1239   0.07303   0.06904  -0.1129   0.8409   0.0909
  -6.500   0.1371   0.07093   0.06691  -0.1140   0.8355   0.0935
  -6.250   0.1520   0.06529   0.06124  -0.1327   0.8261   0.0995
  -6.000   0.1648   0.06334   0.05927  -0.1294   0.8207   0.1003
  -5.750   0.2458   0.02904   0.02335  -0.1915   0.8161   0.0769
  -5.500   0.2758   0.02621   0.02029  -0.1946   0.8092   0.0781
  -5.250   0.3034   0.02556   0.01967  -0.1949   0.8038   0.0801
  -5.000   0.3365   0.02409   0.01793  -0.1967   0.8000   0.0824
  -4.750   0.3694   0.02247   0.01593  -0.1987   0.7948   0.0845
  -4.500   0.4012   0.02138   0.01444  -0.2000   0.7888   0.0868
  -4.250   0.4317   0.02025   0.01323  -0.2009   0.7845   0.0899
  -4.000   0.4630   0.01964   0.01249  -0.2015   0.7807   0.0935
  -3.750   0.4912   0.01914   0.01184  -0.2017   0.7736   0.0971
  -3.500   0.5219   0.01831   0.01086  -0.2023   0.7686   0.1012
  -3.250   0.5528   0.01781   0.01031  -0.2027   0.7648   0.1065
  -3.000   0.5812   0.01756   0.00993  -0.2028   0.7586   0.1118
  -2.750   0.6106   0.01690   0.00931  -0.2032   0.7530   0.1186
  -2.500   0.6416   0.01656   0.00881  -0.2035   0.7487   0.1269
  -2.250   0.6705   0.01609   0.00844  -0.2038   0.7434   0.1370
  -2.000   0.6993   0.01579   0.00816  -0.2040   0.7374   0.1489
  -1.750   0.7297   0.01548   0.00782  -0.2043   0.7326   0.1627
  -1.500   0.7591   0.01532   0.00765  -0.2044   0.7274   0.1777
  -1.250   0.7872   0.01522   0.00760  -0.2044   0.7207   0.1942
  -1.000   0.8173   0.01502   0.00743  -0.2046   0.7153   0.2153
  -0.750   0.8457   0.01497   0.00741  -0.2046   0.7089   0.2452
  -0.500   0.8740   0.01493   0.00743  -0.2045   0.7016   0.2816
  -0.250   0.9040   0.01488   0.00735  -0.2046   0.6959   0.3137
   0.000   0.9301   0.01497   0.00748  -0.2042   0.6875   0.3376
   0.250   0.9591   0.01494   0.00741  -0.2041   0.6808   0.3580
   0.500   0.9860   0.01501   0.00749  -0.2038   0.6725   0.3755
   0.750   1.0140   0.01499   0.00745  -0.2036   0.6645   0.3913
   1.000   1.0408   0.01504   0.00752  -0.2032   0.6554   0.4064
   1.250   1.0687   0.01505   0.00748  -0.2030   0.6463   0.4226
   1.500   1.0944   0.01513   0.00759  -0.2025   0.6353   0.4401
   1.750   1.1220   0.01519   0.00758  -0.2022   0.6256   0.4582
   2.000   1.1472   0.01526   0.00769  -0.2016   0.6137   0.4764
   2.250   1.1729   0.01537   0.00780  -0.2011   0.6019   0.4973
   2.500   1.1997   0.01547   0.00784  -0.2007   0.5912   0.5206
   2.750   1.2239   0.01556   0.00802  -0.2000   0.5786   0.5451
   3.000   1.2488   0.01570   0.00820  -0.1995   0.5672   0.5742
   3.250   1.2748   0.01582   0.00829  -0.1990   0.5576   0.6068
   3.500   1.2984   0.01593   0.00851  -0.1982   0.5456   0.6449
   3.750   1.3222   0.01600   0.00863  -0.1974   0.5352   0.6966
   4.000   1.3420   0.01570   0.00860  -0.1957   0.5260   1.0000
   4.250   1.3670   0.01601   0.00883  -0.1953   0.5167   1.0000
   4.500   1.3924   0.01632   0.00900  -0.1949   0.5094   1.0000
   4.750   1.4169   0.01666   0.00931  -0.1944   0.5020   1.0000
   5.000   1.4416   0.01700   0.00957  -0.1939   0.4952   1.0000
   5.250   1.4670   0.01739   0.00985  -0.1936   0.4895   1.0000
   5.500   1.4908   0.01776   0.01024  -0.1930   0.4834   1.0000
   5.750   1.5159   0.01815   0.01056  -0.1926   0.4779   1.0000
   6.000   1.5414   0.01859   0.01093  -0.1923   0.4728   1.0000
   6.250   1.5642   0.01901   0.01138  -0.1916   0.4671   1.0000
   6.500   1.5887   0.01943   0.01177  -0.1911   0.4616   1.0000
   6.750   1.6148   0.01992   0.01219  -0.1910   0.4566   1.0000
   7.000   1.6361   0.02038   0.01273  -0.1900   0.4512   1.0000
   7.250   1.6597   0.02085   0.01320  -0.1894   0.4461   1.0000
   7.500   1.6883   0.02139   0.01362  -0.1898   0.4414   1.0000
   7.750   1.7075   0.02190   0.01427  -0.1885   0.4365   1.0000
   8.000   1.7284   0.02240   0.01483  -0.1875   0.4310   1.0000
   8.250   1.7543   0.02293   0.01527  -0.1874   0.4252   1.0000
   8.500   1.7709   0.02350   0.01595  -0.1857   0.4189   1.0000
   8.750   1.7881   0.02400   0.01648  -0.1841   0.4120   1.0000
   9.000   1.8129   0.02458   0.01698  -0.1838   0.4054   1.0000
   9.250   1.8222   0.02515   0.01773  -0.1809   0.3992   1.0000
   9.500   1.8388   0.02567   0.01827  -0.1793   0.3932   1.0000
   9.750   1.8580   0.02625   0.01885  -0.1781   0.3870   1.0000
  10.000   1.8605   0.02690   0.01966  -0.1742   0.3810   1.0000
  10.250   1.8725   0.02747   0.02027  -0.1719   0.3751   1.0000
  10.500   1.8861   0.02814   0.02096  -0.1699   0.3693   1.0000
  10.750   1.8871   0.02902   0.02201  -0.1663   0.3630   1.0000
  11.000   1.8960   0.02974   0.02275  -0.1638   0.3567   1.0000
  11.250   1.8998   0.03075   0.02387  -0.1608   0.3503   1.0000
  11.500   1.9014   0.03186   0.02511  -0.1578   0.3434   1.0000
  11.750   1.9088   0.03282   0.02605  -0.1555   0.3368   1.0000
  12.000   1.9057   0.03439   0.02782  -0.1524   0.3290   1.0000
  12.250   1.9101   0.03561   0.02903  -0.1500   0.3219   1.0000
  12.500   1.9079   0.03743   0.03104  -0.1474   0.3135   1.0000
  12.750   1.9095   0.03902   0.03261  -0.1451   0.3060   1.0000
  13.000   1.9087   0.04101   0.03477  -0.1429   0.2974   1.0000
  13.250   1.9084   0.04296   0.03673  -0.1408   0.2895   1.0000
  13.500   1.9065   0.04523   0.03912  -0.1388   0.2803   1.0000
  13.750   1.9030   0.04775   0.04170  -0.1369   0.2706   1.0000
  14.000   1.8981   0.05052   0.04447  -0.1351   0.2607   1.0000
  14.250   1.8935   0.05346   0.04750  -0.1336   0.2502   1.0000
  14.500   1.8852   0.05689   0.05096  -0.1321   0.2384   1.0000
  14.750   1.8744   0.06072   0.05480  -0.1306   0.2259   1.0000
  15.000   1.8612   0.06500   0.05909  -0.1294   0.2124   1.0000
  15.250   1.8461   0.06966   0.06377  -0.1284   0.1975   1.0000
  15.500   1.8278   0.07492   0.06905  -0.1276   0.1781   1.0000
  15.750   1.8033   0.08111   0.07519  -0.1270   0.1548   1.0000
  16.000   1.7730   0.08825   0.08224  -0.1268   0.1318   1.0000
  16.250   1.7415   0.09582   0.08973  -0.1271   0.1125   1.0000
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