Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.89 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe226-il-1000000-n5.txt
Download as CSV file: xf-goe226-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.4712   0.06912   0.06629  -0.1005   0.8335   0.0259
 -13.000  -0.5191   0.05704   0.05403  -0.1118   0.8273   0.0260
 -12.750  -0.5444   0.04697   0.04379  -0.1252   0.8210   0.0262
 -12.500  -0.5405   0.03567   0.03227  -0.1465   0.8158   0.0265
 -12.250  -0.5104   0.02726   0.02363  -0.1647   0.8109   0.0269
 -12.000  -0.4737   0.02235   0.01852  -0.1759   0.8065   0.0273
 -11.750  -0.4370   0.01942   0.01538  -0.1830   0.8025   0.0277
 -11.500  -0.4049   0.01815   0.01400  -0.1859   0.7983   0.0281
 -11.250  -0.3739   0.01719   0.01293  -0.1880   0.7921   0.0284
 -11.000  -0.3436   0.01641   0.01201  -0.1895   0.7854   0.0288
 -10.750  -0.3131   0.01575   0.01125  -0.1908   0.7788   0.0292
 -10.500  -0.2831   0.01518   0.01057  -0.1919   0.7720   0.0295
 -10.250  -0.2531   0.01465   0.00994  -0.1929   0.7655   0.0298
 -10.000  -0.2230   0.01413   0.00931  -0.1938   0.7576   0.0300
  -9.750  -0.1929   0.01354   0.00862  -0.1948   0.7499   0.0305
  -9.500  -0.1628   0.01308   0.00809  -0.1956   0.7417   0.0310
  -9.250  -0.1331   0.01272   0.00764  -0.1962   0.7332   0.0314
  -9.000  -0.1032   0.01239   0.00723  -0.1968   0.7242   0.0318
  -8.750  -0.0735   0.01210   0.00685  -0.1972   0.7157   0.0323
  -8.500  -0.0438   0.01183   0.00650  -0.1977   0.7062   0.0328
  -8.250  -0.0142   0.01160   0.00618  -0.1981   0.6974   0.0333
  -8.000   0.0156   0.01137   0.00587  -0.1985   0.6887   0.0338
  -7.750   0.0452   0.01117   0.00557  -0.1989   0.6816   0.0342
  -7.500   0.0753   0.01089   0.00523  -0.1994   0.6748   0.0348
  -7.250   0.1050   0.01066   0.00494  -0.1998   0.6679   0.0354
  -7.000   0.1349   0.01048   0.00470  -0.2002   0.6617   0.0361
  -6.750   0.1646   0.01031   0.00448  -0.2005   0.6548   0.0368
  -6.250   0.2241   0.01004   0.00409  -0.2011   0.6434   0.0383
  -6.000   0.2538   0.00992   0.00391  -0.2014   0.6374   0.0389
  -5.750   0.2834   0.00978   0.00371  -0.2017   0.6317   0.0400
  -5.500   0.3133   0.00964   0.00355  -0.2020   0.6277   0.0412
  -5.250   0.3431   0.00952   0.00341  -0.2023   0.6236   0.0423
  -5.000   0.3728   0.00943   0.00328  -0.2026   0.6186   0.0434
  -4.750   0.4022   0.00938   0.00316  -0.2028   0.6138   0.0443
  -4.500   0.4321   0.00926   0.00302  -0.2031   0.6104   0.0457
  -4.250   0.4620   0.00915   0.00290  -0.2034   0.6067   0.0473
  -4.000   0.4916   0.00908   0.00281  -0.2036   0.6023   0.0489
  -3.750   0.5209   0.00905   0.00273  -0.2038   0.5969   0.0504
  -3.500   0.5505   0.00898   0.00263  -0.2040   0.5920   0.0525
  -3.250   0.5802   0.00891   0.00255  -0.2043   0.5868   0.0547
  -3.000   0.6094   0.00889   0.00249  -0.2045   0.5803   0.0569
  -2.750   0.6387   0.00885   0.00243  -0.2047   0.5746   0.0598
  -2.500   0.6681   0.00881   0.00239  -0.2049   0.5678   0.0638
  -2.250   0.6970   0.00880   0.00236  -0.2050   0.5603   0.0699
  -2.000   0.7263   0.00877   0.00235  -0.2052   0.5525   0.0782
  -1.750   0.7548   0.00881   0.00235  -0.2053   0.5417   0.0855
  -1.500   0.7831   0.00888   0.00237  -0.2053   0.5263   0.0923
  -1.250   0.8103   0.00905   0.00242  -0.2051   0.5007   0.0959
  -1.000   0.8364   0.00930   0.00252  -0.2048   0.4701   0.1008
  -0.750   0.8631   0.00951   0.00262  -0.2046   0.4509   0.1050
  -0.500   0.8903   0.00967   0.00271  -0.2045   0.4389   0.1075
  -0.250   0.9179   0.00979   0.00279  -0.2044   0.4297   0.1119
   0.000   0.9457   0.00989   0.00286  -0.2044   0.4229   0.1173
   0.250   0.9737   0.00997   0.00293  -0.2043   0.4180   0.1221
   0.500   1.0015   0.01005   0.00301  -0.2043   0.4129   0.1326
   0.750   1.0292   0.01010   0.00311  -0.2044   0.4075   0.1673
   1.000   1.0575   0.01010   0.00321  -0.2045   0.4042   0.2054
   1.250   1.0854   0.01016   0.00331  -0.2045   0.4005   0.2269
   1.500   1.1128   0.01027   0.00343  -0.2044   0.3961   0.2426
   1.750   1.1397   0.01041   0.00356  -0.2043   0.3915   0.2560
   2.000   1.1670   0.01052   0.00369  -0.2042   0.3880   0.2683
   2.250   1.1946   0.01060   0.00379  -0.2041   0.3854   0.2783
   2.500   1.2219   0.01069   0.00391  -0.2040   0.3821   0.2893
   2.750   1.2490   0.01080   0.00404  -0.2039   0.3792   0.3017
   3.000   1.2758   0.01093   0.00418  -0.2037   0.3766   0.3146
   3.250   1.3023   0.01106   0.00433  -0.2035   0.3740   0.3285
   3.500   1.3285   0.01121   0.00450  -0.2033   0.3712   0.3397
   3.750   1.3554   0.01131   0.00463  -0.2031   0.3695   0.3524
   4.000   1.3821   0.01140   0.00478  -0.2030   0.3674   0.3670
   4.250   1.4085   0.01152   0.00494  -0.2028   0.3648   0.3835
   4.500   1.4346   0.01165   0.00512  -0.2025   0.3622   0.4026
   4.750   1.4602   0.01179   0.00531  -0.2022   0.3596   0.4255
   5.000   1.4853   0.01196   0.00551  -0.2018   0.3569   0.4488
   5.250   1.5100   0.01214   0.00573  -0.2013   0.3541   0.4678
   5.500   1.5354   0.01228   0.00592  -0.2009   0.3518   0.4844
   5.750   1.5605   0.01242   0.00611  -0.2005   0.3483   0.5028
   6.000   1.5848   0.01259   0.00634  -0.2000   0.3446   0.5227
   6.250   1.6081   0.01280   0.00659  -0.1993   0.3404   0.5474
   6.750   1.6541   0.01317   0.00714  -0.1979   0.3316   0.6439
   7.000   1.6741   0.01338   0.00742  -0.1966   0.3264   0.6831
   7.250   1.6944   0.01357   0.00779  -0.1955   0.3209   0.7834
   7.500   1.7121   0.01360   0.00805  -0.1937   0.3161   1.0000
   7.750   1.7305   0.01401   0.00844  -0.1922   0.3077   1.0000
   8.000   1.7479   0.01447   0.00886  -0.1907   0.2981   1.0000
   8.250   1.7629   0.01508   0.00941  -0.1888   0.2861   1.0000
   8.500   1.7773   0.01574   0.01002  -0.1869   0.2751   1.0000
   8.750   1.7908   0.01649   0.01072  -0.1850   0.2624   1.0000
   9.000   1.8025   0.01736   0.01153  -0.1828   0.2494   1.0000
   9.250   1.8139   0.01828   0.01239  -0.1807   0.2376   1.0000
   9.500   1.8243   0.01929   0.01335  -0.1786   0.2268   1.0000
   9.750   1.8367   0.02020   0.01424  -0.1768   0.2179   1.0000
  10.000   1.8483   0.02118   0.01520  -0.1749   0.2098   1.0000
  10.250   1.8575   0.02234   0.01632  -0.1728   0.1999   1.0000
  10.500   1.8685   0.02339   0.01736  -0.1710   0.1911   1.0000
  10.750   1.8753   0.02477   0.01869  -0.1688   0.1793   1.0000
  11.000   1.8783   0.02645   0.02029  -0.1662   0.1628   1.0000
  11.250   1.8715   0.02891   0.02259  -0.1628   0.1376   1.0000
  11.500   1.8589   0.03192   0.02545  -0.1590   0.1118   1.0000
  11.750   1.8514   0.03468   0.02813  -0.1560   0.0948   1.0000
  12.000   1.8336   0.03850   0.03181  -0.1525   0.0678   1.0000
  12.250   1.8132   0.04285   0.03605  -0.1492   0.0428   1.0000
  12.500   1.8112   0.04559   0.03880  -0.1475   0.0361   1.0000
  12.750   1.8134   0.04796   0.04121  -0.1461   0.0332   1.0000
  13.000   1.8163   0.05032   0.04361  -0.1448   0.0311   1.0000
  13.250   1.8197   0.05268   0.04602  -0.1437   0.0298   1.0000
  13.500   1.8215   0.05526   0.04866  -0.1425   0.0284   1.0000
  13.750   1.8228   0.05791   0.05135  -0.1414   0.0272   1.0000
  14.000   1.8255   0.06043   0.05394  -0.1405   0.0264   1.0000
  14.250   1.8271   0.06313   0.05671  -0.1396   0.0257   1.0000
  14.500   1.8282   0.06591   0.05954  -0.1387   0.0249   1.0000
  14.750   1.8273   0.06896   0.06266  -0.1379   0.0241   1.0000
  15.000   1.8250   0.07221   0.06597  -0.1371   0.0233   1.0000
  15.250   1.8242   0.07529   0.06911  -0.1364   0.0227   1.0000
  15.500   1.8230   0.07847   0.07237  -0.1358   0.0221   1.0000
  15.750   1.8208   0.08183   0.07580  -0.1353   0.0215   1.0000
  16.000   1.8183   0.08524   0.07928  -0.1348   0.0208   1.0000
  16.250   1.8137   0.08897   0.08309  -0.1345   0.0202   1.0000
  16.500   1.8080   0.09288   0.08707  -0.1342   0.0197   1.0000
  16.750   1.8029   0.09677   0.09104  -0.1341   0.0192   1.0000
  17.000   1.7994   0.10047   0.09482  -0.1340   0.0187   1.0000
  17.250   1.7948   0.10436   0.09879  -0.1341   0.0182   1.0000
  17.500   1.7892   0.10843   0.10294  -0.1343   0.0177   1.0000
  17.750   1.7830   0.11258   0.10716  -0.1347   0.0171   1.0000
<< Back to GOE 226 (MVA H.36) AIRFOIL (goe226-il)

Polar data table (+)

Polar graphs


<< Back to GOE 226 (MVA H.36) AIRFOIL (goe226-il)