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GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il)
Reynolds number: 100,000
Max Cl/Cd: 59.7 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe226-il-100000-n5.txt
Download as CSV file: xf-goe226-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.0274   0.10328   0.09779  -0.1022   0.8993   0.0829
  -9.250   0.0261   0.10116   0.09566  -0.1053   0.8920   0.0834
  -9.000   0.0303   0.09850   0.09300  -0.1072   0.8847   0.0836
  -8.750   0.0363   0.09147   0.08590  -0.1083   0.8786   0.0653
  -8.500   0.0520   0.08902   0.08342  -0.1081   0.8739   0.0645
  -8.250   0.0602   0.08653   0.08093  -0.1087   0.8671   0.0640
  -8.000   0.0643   0.08376   0.07815  -0.1102   0.8597   0.0643
  -7.750   0.0693   0.08069   0.07505  -0.1120   0.8539   0.0646
  -7.500   0.0720   0.07833   0.07271  -0.1126   0.8449   0.0644
  -7.250   0.0787   0.07566   0.07001  -0.1137   0.8391   0.0641
  -7.000   0.0844   0.07297   0.06733  -0.1153   0.8307   0.0638
  -6.750   0.0930   0.06969   0.06402  -0.1180   0.8237   0.0636
  -6.500   0.1019   0.06560   0.05989  -0.1227   0.8167   0.0642
  -6.250   0.1111   0.05887   0.05309  -0.1325   0.8082   0.0652
  -6.000   0.1353   0.05144   0.04553  -0.1440   0.8034   0.0658
  -5.750   0.1763   0.03990   0.03360  -0.1661   0.7951   0.0676
  -5.500   0.2324   0.03229   0.02511  -0.1830   0.7904   0.0716
  -5.250   0.2774   0.02844   0.02045  -0.1902   0.7869   0.0743
  -5.000   0.3036   0.02780   0.01978  -0.1906   0.7802   0.0759
  -4.750   0.3334   0.02700   0.01884  -0.1916   0.7742   0.0787
  -4.500   0.3686   0.02567   0.01711  -0.1936   0.7702   0.0825
  -4.250   0.3979   0.02485   0.01614  -0.1944   0.7647   0.0850
  -4.000   0.4256   0.02440   0.01564  -0.1947   0.7584   0.0881
  -3.750   0.4583   0.02364   0.01464  -0.1957   0.7538   0.0930
  -3.500   0.4874   0.02304   0.01394  -0.1961   0.7477   0.0969
  -3.250   0.5153   0.02263   0.01349  -0.1962   0.7408   0.1016
  -3.000   0.5476   0.02204   0.01268  -0.1969   0.7362   0.1083
  -2.750   0.5753   0.02168   0.01237  -0.1970   0.7302   0.1141
  -2.500   0.6037   0.02139   0.01196  -0.1972   0.7240   0.1222
  -2.250   0.6348   0.02094   0.01153  -0.1977   0.7195   0.1311
  -2.000   0.6634   0.02071   0.01127  -0.1979   0.7139   0.1410
  -1.750   0.6908   0.02058   0.01112  -0.1979   0.7075   0.1526
  -1.500   0.7215   0.02029   0.01083  -0.1983   0.7024   0.1662
  -1.250   0.7491   0.02021   0.01078  -0.1983   0.6959   0.1823
  -1.000   0.7771   0.02013   0.01071  -0.1983   0.6890   0.2035
  -0.750   0.8083   0.01991   0.01052  -0.1986   0.6838   0.2289
  -0.500   0.8336   0.02002   0.01067  -0.1982   0.6757   0.2553
  -0.250   0.8624   0.01997   0.01059  -0.1982   0.6693   0.2808
   0.000   0.8907   0.01998   0.01058  -0.1981   0.6629   0.3040
   0.250   0.9166   0.02009   0.01070  -0.1977   0.6550   0.3249
   0.500   0.9467   0.02002   0.01056  -0.1978   0.6489   0.3445
   0.750   0.9711   0.02021   0.01077  -0.1972   0.6398   0.3608
   1.000   0.9996   0.02020   0.01071  -0.1970   0.6323   0.3794
   1.250   1.0244   0.02038   0.01091  -0.1964   0.6231   0.3995
   1.500   1.0517   0.02045   0.01094  -0.1961   0.6149   0.4226
   1.750   1.0765   0.02063   0.01113  -0.1955   0.6057   0.4439
   2.000   1.1029   0.02073   0.01121  -0.1951   0.5972   0.4645
   2.250   1.1271   0.02091   0.01142  -0.1944   0.5875   0.4836
   2.500   1.1531   0.02100   0.01147  -0.1939   0.5785   0.5026
   2.750   1.1759   0.02123   0.01176  -0.1931   0.5678   0.5221
   3.000   1.2020   0.02130   0.01180  -0.1926   0.5593   0.5456
   3.500   1.2480   0.02173   0.01235  -0.1909   0.5404   0.6033
   4.000   1.2930   0.02206   0.01283  -0.1890   0.5229   0.7002
   4.250   1.3101   0.02200   0.01301  -0.1870   0.5146   1.0000
   4.500   1.3343   0.02235   0.01323  -0.1864   0.5072   1.0000
   4.750   1.3562   0.02277   0.01357  -0.1855   0.4985   1.0000
   5.000   1.3788   0.02314   0.01384  -0.1846   0.4906   1.0000
   5.250   1.3997   0.02360   0.01423  -0.1836   0.4823   1.0000
   5.500   1.4226   0.02399   0.01450  -0.1828   0.4756   1.0000
   5.750   1.4426   0.02453   0.01505  -0.1817   0.4687   1.0000
   6.000   1.4655   0.02498   0.01542  -0.1809   0.4631   1.0000
   6.250   1.4880   0.02547   0.01586  -0.1802   0.4579   1.0000
   6.500   1.5075   0.02607   0.01649  -0.1791   0.4523   1.0000
   6.750   1.5293   0.02658   0.01698  -0.1782   0.4471   1.0000
   7.000   1.5545   0.02705   0.01735  -0.1779   0.4424   1.0000
   7.250   1.5695   0.02775   0.01814  -0.1761   0.4370   1.0000
   7.500   1.5883   0.02837   0.01881  -0.1748   0.4319   1.0000
   7.750   1.6123   0.02889   0.01928  -0.1744   0.4275   1.0000
   8.000   1.6335   0.02952   0.01993  -0.1735   0.4231   1.0000
   8.250   1.6469   0.03033   0.02088  -0.1716   0.4181   1.0000
   8.500   1.6646   0.03104   0.02163  -0.1703   0.4132   1.0000
   8.750   1.6888   0.03157   0.02213  -0.1699   0.4086   1.0000
   9.000   1.7029   0.03243   0.02308  -0.1682   0.4038   1.0000
   9.250   1.7121   0.03343   0.02423  -0.1658   0.3985   1.0000
   9.500   1.7285   0.03420   0.02507  -0.1645   0.3937   1.0000
   9.750   1.7535   0.03473   0.02557  -0.1642   0.3895   1.0000
  10.000   1.7580   0.03599   0.02702  -0.1614   0.3847   1.0000
  10.250   1.7637   0.03724   0.02844  -0.1590   0.3794   1.0000
  10.500   1.7776   0.03809   0.02935  -0.1574   0.3742   1.0000
  10.750   1.7886   0.03909   0.03040  -0.1555   0.3688   1.0000
  11.000   1.7832   0.04095   0.03248  -0.1522   0.3624   1.0000
  11.250   1.7915   0.04203   0.03362  -0.1502   0.3562   1.0000
  11.500   1.7928   0.04365   0.03536  -0.1477   0.3502   1.0000
  11.750   1.7875   0.04580   0.03770  -0.1449   0.3436   1.0000
  12.000   1.7966   0.04689   0.03883  -0.1432   0.3379   1.0000
  12.250   1.7876   0.04959   0.04173  -0.1406   0.3316   1.0000
  12.500   1.7843   0.05186   0.04414  -0.1384   0.3251   1.0000
  12.750   1.7879   0.05355   0.04588  -0.1367   0.3193   1.0000
  13.000   1.7726   0.05722   0.04979  -0.1344   0.3123   1.0000
  13.250   1.7759   0.05901   0.05162  -0.1329   0.3061   1.0000
  13.500   1.7597   0.06319   0.05601  -0.1312   0.2989   1.0000
  13.750   1.7566   0.06593   0.05883  -0.1299   0.2920   1.0000
  14.000   1.7449   0.06993   0.06297  -0.1288   0.2851   1.0000
  14.250   1.7363   0.07365   0.06680  -0.1278   0.2779   1.0000
  14.500   1.7280   0.07747   0.07071  -0.1271   0.2708   1.0000
  14.750   1.7144   0.08213   0.07550  -0.1266   0.2636   1.0000
  15.000   1.7113   0.08537   0.07880  -0.1260   0.2568   1.0000
  15.250   1.6906   0.09139   0.08500  -0.1261   0.2502   1.0000
  15.500   1.6980   0.09313   0.08672  -0.1255   0.2433   1.0000
  15.750   1.6687   0.10078   0.09460  -0.1263   0.2371   1.0000
  16.000   1.6730   0.10300   0.09680  -0.1260   0.2288   1.0000
  16.250   1.6442   0.11095   0.10496  -0.1275   0.2223   1.0000
  16.500   1.6444   0.11399   0.10800  -0.1277   0.2138   1.0000
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