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GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il)
Reynolds number: 100,000
Max Cl/Cd: 51.57 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe228-il-100000-n5.txt
Download as CSV file: xf-goe228-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 228 (MVA H.38) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0571   0.10365   0.09834  -0.1068   0.9407   0.0513
 -11.000  -0.0572   0.09923   0.09392  -0.1088   0.9323   0.0513
 -10.750  -0.0570   0.09325   0.08792  -0.1129   0.9270   0.0515
 -10.500  -0.0477   0.09014   0.08481  -0.1149   0.9209   0.0524
 -10.250  -0.0374   0.08795   0.08262  -0.1158   0.9134   0.0534
  -9.750  -0.2273   0.05015   0.04423  -0.1467   0.8814   0.0516
  -9.500  -0.2145   0.04593   0.03976  -0.1534   0.8755   0.0523
  -9.250  -0.2077   0.04351   0.03715  -0.1552   0.8663   0.0528
  -9.000  -0.1873   0.04076   0.03414  -0.1586   0.8607   0.0537
  -8.750  -0.1598   0.03822   0.03131  -0.1623   0.8570   0.0552
  -8.500  -0.1466   0.03651   0.02934  -0.1627   0.8476   0.0566
  -8.000  -0.0869   0.03242   0.02458  -0.1676   0.8390   0.0598
  -7.750  -0.0676   0.03149   0.02360  -0.1671   0.8305   0.0610
  -7.500  -0.0364   0.03021   0.02217  -0.1685   0.8258   0.0628
  -7.250  -0.0024   0.02892   0.02063  -0.1703   0.8220   0.0655
  -7.000   0.0180   0.02816   0.01970  -0.1697   0.8128   0.0677
  -6.750   0.0489   0.02715   0.01871  -0.1706   0.8078   0.0701
  -6.500   0.0793   0.02625   0.01773  -0.1714   0.8024   0.0729
  -6.250   0.1035   0.02562   0.01698  -0.1711   0.7939   0.0761
  -6.000   0.1362   0.02469   0.01604  -0.1723   0.7887   0.0805
  -5.750   0.1623   0.02412   0.01541  -0.1724   0.7807   0.0857
  -5.250   0.2265   0.02261   0.01376  -0.1746   0.7679   0.1002
  -5.000   0.2513   0.02213   0.01333  -0.1747   0.7579   0.1101
  -4.750   0.2861   0.02140   0.01255  -0.1763   0.7518   0.1261
  -4.500   0.3121   0.02095   0.01217  -0.1766   0.7415   0.1472
  -4.250   0.3460   0.02025   0.01162  -0.1781   0.7345   0.1888
  -4.000   0.3724   0.02011   0.01164  -0.1782   0.7240   0.2403
  -3.750   0.4050   0.01995   0.01139  -0.1789   0.7164   0.2784
  -3.500   0.4303   0.02003   0.01140  -0.1784   0.7051   0.2996
  -3.250   0.4603   0.01996   0.01119  -0.1787   0.6963   0.3178
  -3.000   0.4883   0.01994   0.01102  -0.1786   0.6858   0.3331
  -2.750   0.5161   0.01994   0.01092  -0.1785   0.6754   0.3475
  -2.500   0.5458   0.01987   0.01074  -0.1786   0.6662   0.3617
  -2.250   0.5723   0.01991   0.01070  -0.1784   0.6551   0.3744
  -2.000   0.6018   0.01988   0.01050  -0.1786   0.6455   0.3883
  -1.750   0.6285   0.01990   0.01048  -0.1783   0.6350   0.3995
  -1.500   0.6560   0.01992   0.01040  -0.1782   0.6251   0.4108
  -1.250   0.6841   0.01993   0.01029  -0.1781   0.6157   0.4220
  -1.000   0.7104   0.01999   0.01030  -0.1779   0.6059   0.4305
  -0.750   0.7389   0.02001   0.01019  -0.1780   0.5973   0.4389
  -0.500   0.7648   0.02013   0.01025  -0.1777   0.5879   0.4470
  -0.250   0.7928   0.02020   0.01022  -0.1777   0.5798   0.4554
   0.000   0.8186   0.02035   0.01032  -0.1775   0.5709   0.4641
   0.250   0.8457   0.02048   0.01037  -0.1774   0.5632   0.4731
   0.500   0.8716   0.02066   0.01052  -0.1771   0.5554   0.4838
   0.750   0.8978   0.02085   0.01068  -0.1769   0.5481   0.4948
   1.000   0.9251   0.02104   0.01079  -0.1769   0.5418   0.5062
   1.250   0.9498   0.02129   0.01105  -0.1765   0.5342   0.5197
   1.500   0.9765   0.02151   0.01120  -0.1763   0.5279   0.5344
   1.750   1.0017   0.02178   0.01145  -0.1760   0.5215   0.5497
   2.000   1.0262   0.02206   0.01174  -0.1755   0.5148   0.5658
   2.250   1.0530   0.02231   0.01190  -0.1754   0.5095   0.5828
   2.500   1.0776   0.02262   0.01222  -0.1751   0.5039   0.6002
   2.750   1.1014   0.02293   0.01255  -0.1745   0.4982   0.6180
   3.000   1.1270   0.02321   0.01280  -0.1743   0.4933   0.6363
   3.250   1.1531   0.02349   0.01304  -0.1741   0.4889   0.6545
   3.500   1.1748   0.02385   0.01348  -0.1733   0.4834   0.6721
   3.750   1.1983   0.02416   0.01381  -0.1727   0.4784   0.6908
   4.000   1.2237   0.02442   0.01405  -0.1724   0.4743   0.7109
   4.250   1.2464   0.02474   0.01443  -0.1717   0.4699   0.7323
   4.500   1.2659   0.02508   0.01489  -0.1705   0.4650   0.7568
   4.750   1.2863   0.02531   0.01524  -0.1694   0.4606   0.7923
   5.000   1.3041   0.02529   0.01534  -0.1674   0.4569   1.0000
   5.250   1.3271   0.02580   0.01581  -0.1671   0.4525   1.0000
   5.500   1.3462   0.02638   0.01642  -0.1661   0.4476   1.0000
   5.750   1.3679   0.02686   0.01687  -0.1655   0.4430   1.0000
   6.000   1.3928   0.02727   0.01719  -0.1653   0.4392   1.0000
   6.250   1.4108   0.02786   0.01780  -0.1641   0.4352   1.0000
   6.500   1.4260   0.02853   0.01853  -0.1625   0.4309   1.0000
   6.750   1.4450   0.02912   0.01915  -0.1615   0.4273   1.0000
   7.000   1.4667   0.02965   0.01967  -0.1610   0.4242   1.0000
   7.250   1.4922   0.03010   0.02006  -0.1609   0.4215   1.0000
   7.500   1.5057   0.03092   0.02097  -0.1592   0.4181   1.0000
   7.750   1.5177   0.03181   0.02197  -0.1574   0.4146   1.0000
   8.000   1.5328   0.03260   0.02284  -0.1560   0.4114   1.0000
   8.250   1.5509   0.03328   0.02355  -0.1550   0.4084   1.0000
   8.500   1.5726   0.03383   0.02410  -0.1545   0.4058   1.0000
   8.750   1.5945   0.03441   0.02469  -0.1540   0.4034   1.0000
   9.000   1.5961   0.03582   0.02629  -0.1511   0.4000   1.0000
   9.250   1.6019   0.03710   0.02770  -0.1488   0.3966   1.0000
   9.500   1.6128   0.03815   0.02884  -0.1472   0.3933   1.0000
   9.750   1.6292   0.03893   0.02967  -0.1461   0.3905   1.0000
  10.000   1.6505   0.03948   0.03024  -0.1456   0.3881   1.0000
  10.250   1.6581   0.04081   0.03169  -0.1438   0.3854   1.0000
  10.500   1.6481   0.04322   0.03433  -0.1404   0.3818   1.0000
  10.750   1.6460   0.04532   0.03659  -0.1380   0.3787   1.0000
  11.000   1.6509   0.04700   0.03839  -0.1363   0.3759   1.0000
  11.250   1.6639   0.04813   0.03961  -0.1352   0.3734   1.0000
  11.500   1.6845   0.04871   0.04023  -0.1347   0.3713   1.0000
  11.750   1.6836   0.05093   0.04259  -0.1328   0.3686   1.0000
  12.000   1.6125   0.05944   0.05148  -0.1274   0.3625   1.0000
  12.250   1.6010   0.06298   0.05515  -0.1257   0.3580   1.0000
  12.500   1.6264   0.06282   0.05503  -0.1253   0.3555   1.0000
  12.750   1.6578   0.06213   0.05437  -0.1252   0.3536   1.0000
  13.000   1.4420   0.09187   0.08456  -0.1226   0.3343   1.0000
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