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GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il)
Reynolds number: 500,000
Max Cl/Cd: 109.76 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe226-il-500000.txt
Download as CSV file: xf-goe226-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0187   0.09692   0.09399  -0.0871   0.8541   0.0428
  -9.500  -0.0092   0.09451   0.09155  -0.0882   0.8490   0.0439
  -8.750  -0.0971   0.02578   0.02186  -0.1797   0.8268   0.0429
  -8.500  -0.0641   0.02343   0.01924  -0.1845   0.8208   0.0436
  -8.250  -0.0319   0.02154   0.01704  -0.1881   0.8157   0.0446
  -8.000   0.0000   0.01997   0.01519  -0.1908   0.8096   0.0456
  -7.750   0.0313   0.01878   0.01371  -0.1927   0.8038   0.0463
  -7.500   0.0617   0.01719   0.01185  -0.1945   0.7987   0.0472
  -7.250   0.0910   0.01637   0.01101  -0.1953   0.7922   0.0480
  -7.000   0.1206   0.01579   0.01034  -0.1960   0.7858   0.0489
  -6.750   0.1504   0.01526   0.00967  -0.1966   0.7800   0.0500
  -6.500   0.1802   0.01476   0.00908  -0.1972   0.7729   0.0512
  -6.250   0.2102   0.01433   0.00848  -0.1977   0.7666   0.0524
  -6.000   0.2402   0.01359   0.00761  -0.1984   0.7605   0.0535
  -5.750   0.2699   0.01306   0.00706  -0.1989   0.7537   0.0549
  -5.500   0.2995   0.01275   0.00666  -0.1993   0.7476   0.0563
  -5.250   0.3293   0.01243   0.00629  -0.1997   0.7408   0.0579
  -5.000   0.3589   0.01220   0.00594  -0.1999   0.7341   0.0596
  -4.750   0.3888   0.01174   0.00542  -0.2004   0.7278   0.0618
  -4.500   0.4185   0.01151   0.00518  -0.2008   0.7213   0.0640
  -4.250   0.4481   0.01133   0.00492  -0.2010   0.7156   0.0663
  -4.000   0.4779   0.01110   0.00462  -0.2014   0.7100   0.0688
  -3.750   0.5076   0.01090   0.00443  -0.2017   0.7034   0.0721
  -3.500   0.5369   0.01083   0.00428  -0.2018   0.6977   0.0757
  -3.250   0.5666   0.01065   0.00408  -0.2022   0.6922   0.0799
  -3.000   0.5961   0.01058   0.00400  -0.2024   0.6866   0.0845
  -2.750   0.6255   0.01047   0.00385  -0.2026   0.6815   0.0903
  -2.500   0.6548   0.01045   0.00380  -0.2028   0.6764   0.0971
  -2.250   0.6843   0.01030   0.00367  -0.2031   0.6708   0.1052
  -2.000   0.7132   0.01031   0.00360  -0.2031   0.6651   0.1124
  -1.750   0.7426   0.01018   0.00348  -0.2035   0.6598   0.1225
  -1.500   0.7719   0.01010   0.00341  -0.2037   0.6543   0.1305
  -1.250   0.8009   0.01006   0.00335  -0.2038   0.6487   0.1400
  -1.000   0.8298   0.01003   0.00331  -0.2040   0.6433   0.1514
  -0.750   0.8589   0.00995   0.00331  -0.2042   0.6375   0.1689
  -0.500   0.8877   0.00991   0.00334  -0.2044   0.6313   0.2046
  -0.250   0.9162   0.00993   0.00340  -0.2044   0.6253   0.2417
   0.000   0.9446   0.00994   0.00346  -0.2045   0.6183   0.2665
   0.250   0.9724   0.01003   0.00353  -0.2044   0.6109   0.2877
   0.500   1.0004   0.01007   0.00359  -0.2043   0.6029   0.3044
   0.750   1.0279   0.01016   0.00365  -0.2042   0.5941   0.3183
   1.000   1.0556   0.01020   0.00373  -0.2041   0.5848   0.3316
   1.250   1.0824   0.01032   0.00380  -0.2038   0.5742   0.3438
   1.500   1.1094   0.01040   0.00387  -0.2036   0.5608   0.3566
   1.750   1.1356   0.01052   0.00398  -0.2033   0.5442   0.3716
   2.000   1.1606   0.01072   0.00410  -0.2027   0.5239   0.3858
   2.250   1.1851   0.01095   0.00426  -0.2021   0.5019   0.4008
   2.500   1.2089   0.01125   0.00448  -0.2014   0.4833   0.4187
   2.750   1.2327   0.01156   0.00473  -0.2007   0.4694   0.4382
   3.000   1.2563   0.01189   0.00499  -0.2000   0.4586   0.4578
   3.250   1.2816   0.01210   0.00522  -0.1996   0.4512   0.4778
   3.500   1.3062   0.01236   0.00548  -0.1990   0.4452   0.4996
   3.750   1.3306   0.01262   0.00575  -0.1985   0.4401   0.5243
   4.000   1.3563   0.01277   0.00600  -0.1982   0.4359   0.5559
   4.250   1.3812   0.01296   0.00628  -0.1977   0.4316   0.5980
   4.500   1.4052   0.01319   0.00659  -0.1971   0.4274   0.6499
   5.000   1.4499   0.01321   0.00707  -0.1951   0.4200   1.0000
   5.250   1.4746   0.01345   0.00732  -0.1946   0.4164   1.0000
   5.500   1.4985   0.01375   0.00759  -0.1940   0.4130   1.0000
   5.750   1.5216   0.01410   0.00790  -0.1932   0.4096   1.0000
   6.000   1.5449   0.01449   0.00824  -0.1926   0.4059   1.0000
   6.250   1.5686   0.01471   0.00852  -0.1919   0.4033   1.0000
   6.500   1.5917   0.01496   0.00880  -0.1912   0.4002   1.0000
   6.750   1.6134   0.01526   0.00911  -0.1902   0.3963   1.0000
   7.000   1.6325   0.01564   0.00946  -0.1888   0.3919   1.0000
   7.250   1.6527   0.01604   0.00985  -0.1876   0.3877   1.0000
   7.500   1.6723   0.01631   0.01018  -0.1863   0.3838   1.0000
   7.750   1.6913   0.01663   0.01055  -0.1849   0.3792   1.0000
   8.000   1.7090   0.01707   0.01098  -0.1834   0.3746   1.0000
   8.250   1.7273   0.01755   0.01145  -0.1820   0.3703   1.0000
   8.500   1.7463   0.01789   0.01188  -0.1808   0.3663   1.0000
   8.750   1.7642   0.01832   0.01235  -0.1794   0.3615   1.0000
   9.000   1.7795   0.01891   0.01293  -0.1778   0.3562   1.0000
   9.250   1.7968   0.01941   0.01350  -0.1764   0.3510   1.0000
   9.500   1.8140   0.01993   0.01407  -0.1751   0.3451   1.0000
   9.750   1.8277   0.02066   0.01479  -0.1734   0.3392   1.0000
  10.000   1.8443   0.02126   0.01546  -0.1721   0.3324   1.0000
  10.250   1.8572   0.02208   0.01629  -0.1704   0.3241   1.0000
  10.500   1.8712   0.02287   0.01712  -0.1689   0.3149   1.0000
  10.750   1.8808   0.02397   0.01819  -0.1669   0.3046   1.0000
  11.000   1.8914   0.02505   0.01927  -0.1651   0.2931   1.0000
  11.250   1.8995   0.02632   0.02053  -0.1632   0.2809   1.0000
  11.500   1.9046   0.02784   0.02202  -0.1609   0.2683   1.0000
  11.750   1.9084   0.02950   0.02365  -0.1587   0.2569   1.0000
  12.000   1.9109   0.03131   0.02542  -0.1564   0.2457   1.0000
  12.250   1.9135   0.03315   0.02726  -0.1542   0.2337   1.0000
  12.500   1.9148   0.03516   0.02926  -0.1520   0.2223   1.0000
  12.750   1.9140   0.03743   0.03150  -0.1498   0.2105   1.0000
  13.000   1.9114   0.03995   0.03399  -0.1476   0.1970   1.0000
  13.250   1.9055   0.04289   0.03687  -0.1454   0.1782   1.0000
  13.500   1.8897   0.04692   0.04075  -0.1429   0.1507   1.0000
  13.750   1.8643   0.05216   0.04580  -0.1402   0.1209   1.0000
  14.000   1.8385   0.05768   0.05121  -0.1379   0.0971   1.0000
  14.250   1.8099   0.06379   0.05721  -0.1360   0.0717   1.0000
  14.500   1.7828   0.06997   0.06332  -0.1345   0.0525   1.0000
  14.750   1.7663   0.07503   0.06840  -0.1335   0.0454   1.0000
  15.000   1.7550   0.07958   0.07302  -0.1328   0.0418   1.0000
  15.250   1.7438   0.08420   0.07772  -0.1323   0.0395   1.0000
  15.500   1.7327   0.08892   0.08253  -0.1320   0.0377   1.0000
  15.750   1.7250   0.09321   0.08693  -0.1318   0.0365   1.0000
  16.000   1.7157   0.09784   0.09166  -0.1318   0.0353   1.0000
  16.250   1.7045   0.10280   0.09671  -0.1320   0.0343   1.0000
  16.500   1.6921   0.10803   0.10204  -0.1325   0.0334   1.0000
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