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GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il)
Reynolds number: 100,000
Max Cl/Cd: 58.64 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe227-il-100000-n5.txt
Download as CSV file: xf-goe227-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 227 (MVA H.37) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0480   0.12041   0.11505  -0.0971   0.9258   0.0760
 -10.750  -0.0429   0.11744   0.11205  -0.1006   0.9190   0.0763
 -10.500  -0.0361   0.11421   0.10881  -0.1028   0.9102   0.0763
 -10.000  -0.0195   0.10743   0.10196  -0.1070   0.8943   0.0764
  -9.500   0.0048   0.09837   0.09280  -0.1084   0.8803   0.0651
  -9.250   0.0188   0.09540   0.08978  -0.1091   0.8737   0.0641
  -9.000   0.0271   0.09248   0.08682  -0.1102   0.8653   0.0632
  -8.750   0.0343   0.08941   0.08371  -0.1117   0.8575   0.0626
  -8.500   0.0398   0.08636   0.08064  -0.1134   0.8494   0.0632
  -8.250   0.0441   0.08316   0.07742  -0.1154   0.8409   0.0639
  -8.000   0.0494   0.07992   0.07414  -0.1173   0.8333   0.0640
  -7.750   0.0542   0.07688   0.07108  -0.1187   0.8246   0.0638
  -7.500   0.0590   0.07360   0.06775  -0.1206   0.8179   0.0637
  -7.250   0.0605   0.07049   0.06464  -0.1224   0.8086   0.0637
  -6.750   0.0612   0.04954   0.04348  -0.1520   0.7916   0.0660
  -6.500   0.0994   0.03992   0.03340  -0.1724   0.7858   0.0675
  -6.250   0.1351   0.03587   0.02897  -0.1812   0.7798   0.0693
  -6.000   0.1731   0.03260   0.02525  -0.1886   0.7740   0.0724
  -5.750   0.2188   0.02904   0.02081  -0.1968   0.7700   0.0764
  -5.500   0.2516   0.02770   0.01934  -0.1990   0.7667   0.0784
  -5.250   0.2798   0.02697   0.01852  -0.2002   0.7609   0.0808
  -5.000   0.3117   0.02611   0.01743  -0.2020   0.7565   0.0846
  -4.750   0.3468   0.02505   0.01593  -0.2042   0.7531   0.0886
  -4.500   0.3785   0.02427   0.01513  -0.2055   0.7504   0.0917
  -4.250   0.4060   0.02398   0.01479  -0.2060   0.7457   0.0956
  -4.000   0.4363   0.02349   0.01412  -0.2070   0.7415   0.1000
  -3.750   0.4673   0.02296   0.01346  -0.2079   0.7381   0.1039
  -3.500   0.4983   0.02259   0.01307  -0.2088   0.7354   0.1086
  -3.250   0.5281   0.02231   0.01268  -0.2094   0.7323   0.1134
  -3.000   0.5560   0.02214   0.01246  -0.2098   0.7285   0.1180
  -2.750   0.5848   0.02197   0.01232  -0.2104   0.7252   0.1236
  -2.500   0.6151   0.02174   0.01199  -0.2109   0.7219   0.1297
  -2.250   0.6473   0.02136   0.01157  -0.2118   0.7187   0.1363
  -2.000   0.6743   0.02129   0.01149  -0.2120   0.7131   0.1450
  -1.750   0.7035   0.02106   0.01127  -0.2124   0.7080   0.1546
  -1.500   0.7356   0.02073   0.01092  -0.2133   0.7041   0.1686
  -1.250   0.7673   0.02046   0.01076  -0.2144   0.7003   0.1948
  -1.000   0.7945   0.02047   0.01107  -0.2147   0.6947   0.2538
  -0.750   0.8238   0.02049   0.01107  -0.2149   0.6900   0.3084
  -0.500   0.8551   0.02047   0.01097  -0.2153   0.6863   0.3425
  -0.250   0.8804   0.02074   0.01124  -0.2149   0.6814   0.3664
   0.000   0.9070   0.02095   0.01143  -0.2148   0.6769   0.3865
   0.250   0.9355   0.02105   0.01155  -0.2148   0.6730   0.4089
   0.500   0.9658   0.02110   0.01156  -0.2151   0.6698   0.4312
   0.750   0.9899   0.02142   0.01195  -0.2145   0.6649   0.4485
   1.000   1.0157   0.02163   0.01217  -0.2142   0.6601   0.4618
   1.250   1.0448   0.02170   0.01219  -0.2143   0.6559   0.4750
   1.500   1.0760   0.02169   0.01214  -0.2148   0.6525   0.4877
   1.750   1.0977   0.02207   0.01260  -0.2139   0.6466   0.4990
   2.000   1.1241   0.02225   0.01276  -0.2137   0.6414   0.5113
   2.250   1.1539   0.02226   0.01274  -0.2139   0.6371   0.5223
   2.500   1.1798   0.02247   0.01296  -0.2136   0.6320   0.5339
   2.750   1.2026   0.02277   0.01332  -0.2128   0.6257   0.5470
   3.000   1.2310   0.02282   0.01335  -0.2128   0.6205   0.5619
   3.250   1.2581   0.02294   0.01348  -0.2126   0.6152   0.5794
   3.500   1.2781   0.02330   0.01396  -0.2114   0.6080   0.5979
   3.750   1.3055   0.02333   0.01404  -0.2112   0.6024   0.6197
   4.000   1.3284   0.02352   0.01434  -0.2104   0.5959   0.6450
   4.250   1.3478   0.02376   0.01476  -0.2089   0.5880   0.6766
   4.750   1.3817   0.02385   0.01529  -0.2048   0.5731   1.0000
   5.000   1.4080   0.02401   0.01539  -0.2045   0.5662   1.0000
   5.250   1.4220   0.02461   0.01607  -0.2024   0.5563   1.0000
   5.500   1.4462   0.02476   0.01618  -0.2017   0.5486   1.0000
   5.750   1.4563   0.02547   0.01698  -0.1991   0.5372   1.0000
   6.000   1.4723   0.02593   0.01747  -0.1972   0.5276   1.0000
   6.250   1.4879   0.02635   0.01791  -0.1953   0.5180   1.0000
   6.500   1.4968   0.02705   0.01866  -0.1924   0.5071   1.0000
   6.750   1.5127   0.02751   0.01910  -0.1905   0.4978   1.0000
   7.000   1.5282   0.02801   0.01960  -0.1887   0.4885   1.0000
   7.250   1.5432   0.02861   0.02020  -0.1869   0.4796   1.0000
   7.500   1.5622   0.02902   0.02056  -0.1855   0.4720   1.0000
   7.750   1.5767   0.02975   0.02130  -0.1838   0.4639   1.0000
   8.000   1.5955   0.03024   0.02176  -0.1825   0.4568   1.0000
   8.250   1.6104   0.03103   0.02256  -0.1808   0.4495   1.0000
   8.500   1.6275   0.03172   0.02325  -0.1794   0.4429   1.0000
   8.750   1.6495   0.03218   0.02367  -0.1786   0.4375   1.0000
   9.000   1.6608   0.03328   0.02488  -0.1767   0.4309   1.0000
   9.250   1.6805   0.03389   0.02548  -0.1756   0.4250   1.0000
   9.500   1.6987   0.03463   0.02624  -0.1745   0.4191   1.0000
   9.750   1.7091   0.03581   0.02752  -0.1726   0.4125   1.0000
  10.000   1.7311   0.03632   0.02801  -0.1718   0.4065   1.0000
  10.250   1.7362   0.03777   0.02958  -0.1694   0.3988   1.0000
  10.500   1.7472   0.03877   0.03056  -0.1674   0.3894   1.0000
  10.750   1.7451   0.04067   0.03258  -0.1645   0.3801   1.0000
  11.000   1.7522   0.04189   0.03375  -0.1623   0.3696   1.0000
  11.250   1.7438   0.04440   0.03644  -0.1592   0.3599   1.0000
  11.500   1.7452   0.04619   0.03826  -0.1569   0.3502   1.0000
  11.750   1.7406   0.04863   0.04085  -0.1545   0.3410   1.0000
  12.000   1.7396   0.05082   0.04312  -0.1524   0.3321   1.0000
  12.250   1.7357   0.05338   0.04578  -0.1504   0.3228   1.0000
  12.500   1.7312   0.05617   0.04870  -0.1485   0.3136   1.0000
  12.750   1.7291   0.05874   0.05133  -0.1469   0.3043   1.0000
  13.000   1.7223   0.06213   0.05490  -0.1454   0.2951   1.0000
  13.250   1.7176   0.06526   0.05811  -0.1440   0.2851   1.0000
  13.500   1.7093   0.06899   0.06196  -0.1429   0.2737   1.0000
  13.750   1.6997   0.07305   0.06615  -0.1419   0.2615   1.0000
  14.000   1.6902   0.07718   0.07037  -0.1410   0.2484   1.0000
  14.250   1.6796   0.08151   0.07477  -0.1403   0.2340   1.0000
  14.500   1.6665   0.08626   0.07954  -0.1397   0.2169   1.0000
  14.750   1.6500   0.09156   0.08479  -0.1393   0.1970   1.0000
  15.000   1.6309   0.09736   0.09054  -0.1391   0.1747   1.0000
  15.250   1.6092   0.10371   0.09679  -0.1394   0.1543   1.0000
  15.500   1.5876   0.11029   0.10330  -0.1400   0.1368   1.0000
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