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GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il)
Reynolds number: 200,000
Max Cl/Cd: 88 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe227-il-200000.txt
Download as CSV file: xf-goe227-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0224   0.10294   0.09912  -0.1076   0.9271   0.0713
  -9.750   0.0050   0.10128   0.09745  -0.1147   0.9135   0.0736
  -9.500   0.0143   0.09689   0.09304  -0.1149   0.9063   0.0743
  -9.250   0.0343   0.09410   0.09021  -0.1124   0.8974   0.0753
  -9.000   0.0488   0.09176   0.08782  -0.1117   0.8892   0.0765
  -8.750   0.0588   0.08957   0.08559  -0.1118   0.8786   0.0781
  -8.500   0.0669   0.08726   0.08324  -0.1125   0.8685   0.0803
  -8.250   0.0555   0.08487   0.08080  -0.1193   0.8559   0.0847
  -8.000   0.0524   0.08093   0.07685  -0.1234   0.8440   0.0854
  -7.750   0.0737   0.07827   0.07412  -0.1200   0.8377   0.0865
  -7.500   0.0912   0.07652   0.07233  -0.1186   0.8290   0.0879
  -7.250   0.1051   0.07459   0.07033  -0.1187   0.8220   0.0900
  -7.000   0.1145   0.07240   0.06813  -0.1200   0.8128   0.0928
  -6.750   0.1124   0.06638   0.06206  -0.1362   0.8043   0.0985
  -6.500   0.1261   0.06480   0.06048  -0.1326   0.7975   0.0994
  -6.250   0.1628   0.04171   0.03689  -0.1762   0.7911   0.0847
  -6.000   0.1857   0.03780   0.03293  -0.1797   0.7857   0.0825
  -5.750   0.2437   0.02741   0.02149  -0.2003   0.7804   0.0812
  -5.500   0.2840   0.02483   0.01828  -0.2055   0.7763   0.0842
  -5.250   0.3204   0.02260   0.01563  -0.2090   0.7731   0.0866
  -5.000   0.3504   0.02181   0.01480  -0.2102   0.7690   0.0893
  -4.750   0.3807   0.02127   0.01416  -0.2112   0.7648   0.0931
  -4.500   0.4136   0.02063   0.01322  -0.2127   0.7613   0.0970
  -4.250   0.4461   0.01954   0.01198  -0.2142   0.7584   0.1006
  -4.000   0.4772   0.01919   0.01155  -0.2150   0.7559   0.1051
  -3.750   0.5070   0.01890   0.01116  -0.2157   0.7519   0.1097
  -3.500   0.5373   0.01830   0.01045  -0.2165   0.7472   0.1139
  -3.250   0.5676   0.01790   0.01004  -0.2171   0.7431   0.1190
  -3.000   0.5991   0.01759   0.00959  -0.2177   0.7399   0.1243
  -2.750   0.6288   0.01724   0.00920  -0.2183   0.7362   0.1295
  -2.500   0.6577   0.01699   0.00902  -0.2187   0.7320   0.1354
  -2.250   0.6878   0.01681   0.00876  -0.2192   0.7284   0.1418
  -2.000   0.7191   0.01640   0.00839  -0.2200   0.7252   0.1500
  -1.750   0.7505   0.01621   0.00810  -0.2206   0.7221   0.1595
  -1.500   0.7796   0.01598   0.00803  -0.2212   0.7177   0.1741
  -1.250   0.8108   0.01566   0.00790  -0.2222   0.7136   0.2068
  -1.000   0.8422   0.01554   0.00805  -0.2230   0.7099   0.3160
  -0.750   0.8724   0.01569   0.00815  -0.2232   0.7071   0.3592
  -0.500   0.8998   0.01594   0.00839  -0.2232   0.7034   0.3832
  -0.250   0.9270   0.01612   0.00859  -0.2231   0.6994   0.4008
   0.000   0.9554   0.01623   0.00870  -0.2231   0.6958   0.4155
   0.250   0.9848   0.01629   0.00875  -0.2233   0.6925   0.4303
   0.500   1.0142   0.01640   0.00883  -0.2235   0.6892   0.4434
   0.750   1.0399   0.01659   0.00908  -0.2232   0.6845   0.4559
   1.000   1.0675   0.01673   0.00923  -0.2232   0.6801   0.4715
   1.250   1.0968   0.01679   0.00929  -0.2233   0.6764   0.4855
   1.500   1.1262   0.01688   0.00936  -0.2235   0.6727   0.4956
   1.750   1.1514   0.01708   0.00961  -0.2231   0.6673   0.5065
   2.000   1.1791   0.01713   0.00970  -0.2231   0.6623   0.5175
   2.250   1.2097   0.01716   0.00967  -0.2234   0.6580   0.5299
   2.500   1.2351   0.01736   0.00994  -0.2231   0.6526   0.5434
   2.750   1.2617   0.01746   0.01010  -0.2229   0.6469   0.5586
   3.000   1.2919   0.01747   0.01007  -0.2232   0.6418   0.5751
   3.250   1.3172   0.01761   0.01032  -0.2228   0.6355   0.5932
   3.500   1.3433   0.01764   0.01044  -0.2224   0.6287   0.6152
   3.750   1.3741   0.01762   0.01041  -0.2229   0.6233   0.6443
   4.000   1.3957   0.01773   0.01075  -0.2218   0.6155   0.6784
   4.250   1.4219   0.01764   0.01078  -0.2212   0.6086   0.7356
   4.500   1.4399   0.01738   0.01080  -0.2190   0.6012   1.0000
   4.750   1.4657   0.01751   0.01088  -0.2187   0.5926   1.0000
   5.000   1.4918   0.01766   0.01098  -0.2184   0.5847   1.0000
   5.250   1.5152   0.01777   0.01110  -0.2176   0.5750   1.0000
   5.500   1.5382   0.01791   0.01123  -0.2167   0.5655   1.0000
   5.750   1.5620   0.01796   0.01126  -0.2158   0.5558   1.0000
   6.000   1.5815   0.01815   0.01150  -0.2144   0.5440   1.0000
   6.250   1.6032   0.01830   0.01164  -0.2132   0.5335   1.0000
   6.500   1.6244   0.01846   0.01178  -0.2120   0.5229   1.0000
   6.750   1.6429   0.01874   0.01209  -0.2104   0.5107   1.0000
   7.000   1.6619   0.01903   0.01236  -0.2088   0.4995   1.0000
   7.250   1.6809   0.01935   0.01260  -0.2073   0.4893   1.0000
   7.500   1.6983   0.01979   0.01301  -0.2055   0.4788   1.0000
   7.750   1.7152   0.02029   0.01347  -0.2038   0.4689   1.0000
   8.000   1.7321   0.02082   0.01387  -0.2019   0.4587   1.0000
   8.250   1.7428   0.02145   0.01449  -0.1991   0.4478   1.0000
   8.500   1.7552   0.02215   0.01516  -0.1966   0.4374   1.0000
   8.750   1.7716   0.02286   0.01572  -0.1949   0.4272   1.0000
   9.000   1.7797   0.02365   0.01662  -0.1919   0.4184   1.0000
   9.250   1.7964   0.02439   0.01726  -0.1903   0.4098   1.0000
   9.500   1.8024   0.02529   0.01828  -0.1872   0.4012   1.0000
   9.750   1.8164   0.02611   0.01903  -0.1853   0.3929   1.0000
  10.000   1.8223   0.02709   0.02016  -0.1823   0.3853   1.0000
  10.250   1.8352   0.02797   0.02096  -0.1804   0.3773   1.0000
  10.500   1.8359   0.02923   0.02241  -0.1771   0.3689   1.0000
  10.750   1.8425   0.03039   0.02354  -0.1745   0.3601   1.0000
  11.000   1.8442   0.03182   0.02514  -0.1717   0.3515   1.0000
  11.250   1.8483   0.03323   0.02655  -0.1691   0.3430   1.0000
  11.500   1.8486   0.03496   0.02841  -0.1665   0.3330   1.0000
  11.750   1.8472   0.03690   0.03042  -0.1638   0.3218   1.0000
  12.000   1.8440   0.03908   0.03264  -0.1612   0.3099   1.0000
  12.250   1.8386   0.04160   0.03520  -0.1586   0.2962   1.0000
  12.500   1.8313   0.04449   0.03814  -0.1562   0.2784   1.0000
  12.750   1.8187   0.04811   0.04173  -0.1537   0.2540   1.0000
  13.000   1.8007   0.05249   0.04598  -0.1513   0.2244   1.0000
  13.250   1.7771   0.05771   0.05101  -0.1490   0.1907   1.0000
  13.500   1.7497   0.06361   0.05669  -0.1469   0.1543   1.0000
  13.750   1.7213   0.06981   0.06269  -0.1450   0.1253   1.0000
  14.000   1.6968   0.07577   0.06853  -0.1436   0.0999   1.0000
  14.250   1.6689   0.08233   0.07491  -0.1424   0.0654   1.0000
  14.500   1.6470   0.08832   0.08082  -0.1417   0.0545   1.0000
  14.750   1.6311   0.09372   0.08626  -0.1412   0.0494   1.0000
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