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GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.52 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe226-il-1000000.txt
Download as CSV file: xf-goe226-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1272   0.11566   0.11336  -0.0740   0.8560   0.0275
 -11.750  -0.1139   0.11410   0.11177  -0.0743   0.8516   0.0277
 -11.500  -0.4357   0.03140   0.02826  -0.1547   0.8439   0.0309
 -11.250  -0.3979   0.02541   0.02199  -0.1692   0.8393   0.0312
 -11.000  -0.3562   0.02042   0.01662  -0.1818   0.8346   0.0318
 -10.750  -0.3247   0.01898   0.01508  -0.1849   0.8301   0.0324
 -10.500  -0.2942   0.01816   0.01421  -0.1866   0.8253   0.0328
 -10.250  -0.2640   0.01751   0.01349  -0.1879   0.8206   0.0333
 -10.000  -0.2339   0.01687   0.01273  -0.1892   0.8156   0.0338
  -9.750  -0.2035   0.01615   0.01192  -0.1905   0.8110   0.0343
  -9.500  -0.1732   0.01548   0.01115  -0.1917   0.8057   0.0348
  -9.250  -0.1433   0.01492   0.01046  -0.1926   0.8002   0.0353
  -9.000  -0.1132   0.01443   0.00987  -0.1934   0.7947   0.0357
  -8.750  -0.0830   0.01372   0.00905  -0.1944   0.7886   0.0361
  -8.500  -0.0531   0.01299   0.00822  -0.1953   0.7824   0.0370
  -8.250  -0.0231   0.01263   0.00783  -0.1959   0.7764   0.0377
  -8.000   0.0067   0.01230   0.00744  -0.1964   0.7697   0.0383
  -7.750   0.0364   0.01200   0.00704  -0.1969   0.7633   0.0390
  -7.500   0.0665   0.01167   0.00666  -0.1974   0.7565   0.0397
  -7.250   0.0962   0.01141   0.00629  -0.1978   0.7490   0.0403
  -7.000   0.1261   0.01118   0.00599  -0.1981   0.7415   0.0408
  -6.750   0.1562   0.01066   0.00538  -0.1988   0.7332   0.0419
  -6.500   0.1861   0.01039   0.00507  -0.1993   0.7256   0.0429
  -6.250   0.2158   0.01023   0.00485  -0.1996   0.7170   0.0439
  -6.000   0.2454   0.01007   0.00462  -0.1998   0.7091   0.0450
  -5.750   0.2751   0.00992   0.00440  -0.2001   0.7010   0.0459
  -5.500   0.3047   0.00978   0.00417  -0.2004   0.6941   0.0467
  -5.250   0.3350   0.00944   0.00380  -0.2009   0.6871   0.0485
  -5.000   0.3645   0.00933   0.00363  -0.2012   0.6802   0.0500
  -4.750   0.3944   0.00921   0.00347  -0.2015   0.6747   0.0515
  -4.500   0.4240   0.00914   0.00335  -0.2017   0.6690   0.0527
  -4.250   0.4538   0.00893   0.00309  -0.2021   0.6633   0.0554
  -4.000   0.4836   0.00883   0.00297  -0.2024   0.6580   0.0576
  -3.750   0.5132   0.00876   0.00286  -0.2026   0.6523   0.0595
  -3.500   0.5428   0.00864   0.00270  -0.2029   0.6469   0.0628
  -3.250   0.5724   0.00857   0.00261  -0.2031   0.6419   0.0662
  -3.000   0.6022   0.00848   0.00252  -0.2034   0.6370   0.0707
  -2.750   0.6316   0.00845   0.00247  -0.2036   0.6321   0.0762
  -2.500   0.6607   0.00843   0.00245  -0.2037   0.6271   0.0841
  -2.250   0.6905   0.00837   0.00241  -0.2040   0.6231   0.0919
  -2.000   0.7197   0.00837   0.00241  -0.2041   0.6184   0.0984
  -1.750   0.7489   0.00834   0.00238  -0.2043   0.6133   0.1055
  -1.500   0.7779   0.00836   0.00237  -0.2044   0.6084   0.1106
  -1.250   0.8074   0.00833   0.00234  -0.2047   0.6035   0.1159
  -1.000   0.8365   0.00831   0.00232  -0.2048   0.5976   0.1224
  -0.750   0.8650   0.00835   0.00232  -0.2049   0.5913   0.1270
  -0.500   0.8944   0.00830   0.00230  -0.2051   0.5844   0.1379
  -0.250   0.9229   0.00831   0.00232  -0.2052   0.5760   0.1565
   0.000   0.9521   0.00823   0.00236  -0.2055   0.5674   0.2024
   0.250   0.9802   0.00828   0.00242  -0.2055   0.5562   0.2332
   0.500   1.0079   0.00837   0.00249  -0.2055   0.5406   0.2543
   0.750   1.0347   0.00853   0.00259  -0.2053   0.5153   0.2715
   1.000   1.0591   0.00890   0.00277  -0.2047   0.4792   0.2852
   1.250   1.0840   0.00923   0.00298  -0.2041   0.4562   0.2976
   1.500   1.1099   0.00947   0.00316  -0.2038   0.4430   0.3091
   2.000   1.1632   0.00983   0.00347  -0.2034   0.4275   0.3338
   2.250   1.1900   0.00998   0.00362  -0.2032   0.4218   0.3465
   2.500   1.2172   0.01010   0.00375  -0.2031   0.4175   0.3602
   2.750   1.2439   0.01024   0.00391  -0.2029   0.4135   0.3771
   3.250   1.2963   0.01058   0.00428  -0.2024   0.4056   0.4133
   3.500   1.3237   0.01066   0.00443  -0.2023   0.4032   0.4348
   3.750   1.3505   0.01077   0.00458  -0.2021   0.4004   0.4551
   4.000   1.3768   0.01091   0.00476  -0.2019   0.3975   0.4750
   4.250   1.4026   0.01107   0.00496  -0.2016   0.3946   0.4959
   4.500   1.4277   0.01127   0.00518  -0.2011   0.3913   0.5163
   4.750   1.4528   0.01145   0.00542  -0.2007   0.3883   0.5453
   5.000   1.4795   0.01151   0.00561  -0.2006   0.3866   0.5925
   5.250   1.5058   0.01159   0.00582  -0.2004   0.3845   0.6476
   5.500   1.5315   0.01169   0.00602  -0.2001   0.3820   0.6981
   5.750   1.5531   0.01146   0.00622  -0.1990   0.3791   1.0000
   6.000   1.5766   0.01173   0.00645  -0.1983   0.3748   1.0000
   6.250   1.5997   0.01200   0.00672  -0.1975   0.3707   1.0000
   6.500   1.6252   0.01214   0.00688  -0.1972   0.3683   1.0000
   6.750   1.6498   0.01231   0.00706  -0.1967   0.3645   1.0000
   7.000   1.6724   0.01255   0.00730  -0.1959   0.3601   1.0000
   7.250   1.6921   0.01287   0.00759  -0.1945   0.3560   1.0000
   7.500   1.7136   0.01310   0.00784  -0.1935   0.3526   1.0000
   7.750   1.7360   0.01330   0.00808  -0.1926   0.3487   1.0000
   8.000   1.7564   0.01358   0.00837  -0.1915   0.3441   1.0000
   8.250   1.7741   0.01401   0.00877  -0.1899   0.3385   1.0000
   8.500   1.7957   0.01427   0.00906  -0.1890   0.3331   1.0000
   8.750   1.8142   0.01467   0.00945  -0.1877   0.3257   1.0000
   9.000   1.8321   0.01513   0.00990  -0.1863   0.3179   1.0000
   9.250   1.8477   0.01572   0.01045  -0.1846   0.3071   1.0000
   9.500   1.8634   0.01633   0.01103  -0.1830   0.2954   1.0000
   9.750   1.8754   0.01717   0.01181  -0.1809   0.2810   1.0000
  10.000   1.8854   0.01816   0.01273  -0.1787   0.2662   1.0000
  10.250   1.8940   0.01928   0.01377  -0.1763   0.2518   1.0000
  10.500   1.9020   0.02046   0.01489  -0.1739   0.2385   1.0000
  10.750   1.9097   0.02169   0.01608  -0.1716   0.2266   1.0000
  11.000   1.9159   0.02306   0.01739  -0.1692   0.2147   1.0000
  11.250   1.9241   0.02432   0.01862  -0.1672   0.2042   1.0000
  11.500   1.9306   0.02572   0.01999  -0.1650   0.1924   1.0000
  11.750   1.9324   0.02750   0.02169  -0.1624   0.1765   1.0000
  12.000   1.9227   0.03022   0.02424  -0.1588   0.1486   1.0000
  12.250   1.9024   0.03391   0.02773  -0.1545   0.1179   1.0000
  12.500   1.8832   0.03779   0.03147  -0.1508   0.0919   1.0000
  12.750   1.8551   0.04279   0.03630  -0.1470   0.0601   1.0000
  13.000   1.8369   0.04716   0.04059  -0.1443   0.0418   1.0000
  13.250   1.8324   0.05027   0.04372  -0.1426   0.0365   1.0000
  13.500   1.8304   0.05322   0.04671  -0.1412   0.0338   1.0000
  13.750   1.8305   0.05600   0.04955  -0.1401   0.0319   1.0000
  14.000   1.8309   0.05877   0.05238  -0.1390   0.0307   1.0000
  14.250   1.8293   0.06180   0.05547  -0.1379   0.0295   1.0000
  14.500   1.8249   0.06523   0.05897  -0.1369   0.0283   1.0000
  14.750   1.8237   0.06834   0.06216  -0.1361   0.0275   1.0000
  15.000   1.8234   0.07136   0.06525  -0.1353   0.0268   1.0000
  15.250   1.8212   0.07461   0.06857  -0.1346   0.0260   1.0000
  15.500   1.8162   0.07829   0.07233  -0.1340   0.0253   1.0000
  15.750   1.8094   0.08226   0.07638  -0.1334   0.0246   1.0000
  16.000   1.7996   0.08673   0.08093  -0.1330   0.0239   1.0000
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