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GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 448 AIRFOIL (goe448-il)
Reynolds number: 500,000
Max Cl/Cd: 119.35 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe448-il-500000.txt
Download as CSV file: xf-goe448-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 448 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.2146   0.09771   0.09432  -0.1345   0.7879   0.0276
  -9.750   0.2162   0.09503   0.09159  -0.1383   0.7834   0.0288
  -9.500   0.2254   0.09181   0.08835  -0.1393   0.7794   0.0290
  -9.250   0.2388   0.08942   0.08596  -0.1394   0.7749   0.0293
  -9.000   0.2509   0.08741   0.08393  -0.1402   0.7706   0.0298
  -8.750   0.2624   0.08541   0.08188  -0.1412   0.7666   0.0305
  -8.500   0.2734   0.08325   0.07971  -0.1426   0.7625   0.0317
  -8.250   0.2722   0.08079   0.07728  -0.1484   0.7573   0.0336
  -8.000   0.2869   0.07754   0.07400  -0.1477   0.7536   0.0339
  -7.750   0.3008   0.07554   0.07194  -0.1479   0.7498   0.0343
  -7.500   0.3136   0.07368   0.07009  -0.1488   0.7457   0.0349
  -7.250   0.3255   0.07178   0.06820  -0.1499   0.7415   0.0359
  -7.000   0.3350   0.06986   0.06626  -0.1513   0.7374   0.0375
  -6.750   0.3486   0.06616   0.06249  -0.1601   0.7333   0.0391
  -6.500   0.3629   0.06418   0.06053  -0.1594   0.7295   0.0395
  -6.250   0.3793   0.06238   0.05872  -0.1604   0.7254   0.0401
  -6.000   0.3973   0.06048   0.05680  -0.1626   0.7216   0.0410
  -5.750   0.4399   0.05620   0.05238  -0.1798   0.7177   0.0446
  -5.500   0.4508   0.05369   0.04989  -0.1783   0.7142   0.0450
  -5.250   0.4671   0.05201   0.04821  -0.1780   0.7103   0.0454
  -5.000   0.4874   0.05033   0.04650  -0.1793   0.7065   0.0461
  -4.750   0.5116   0.04848   0.04458  -0.1821   0.7030   0.0473
  -4.500   0.5722   0.04282   0.03871  -0.1998   0.6996   0.0511
  -4.250   0.5883   0.04106   0.03697  -0.1992   0.6959   0.0516
  -4.000   0.6092   0.03967   0.03556  -0.1997   0.6922   0.0520
  -3.750   0.6342   0.03820   0.03404  -0.2012   0.6886   0.0528
  -3.500   0.6643   0.03651   0.03223  -0.2042   0.6852   0.0542
  -3.250   0.7270   0.02769   0.02301  -0.2191   0.6822   0.0517
  -3.000   0.7546   0.02641   0.02168  -0.2205   0.6786   0.0522
  -2.750   0.7760   0.02756   0.02287  -0.2191   0.6749   0.0566
  -2.500   0.8328   0.01699   0.01110  -0.2300   0.6723   0.0592
  -2.250   0.8603   0.01726   0.01140  -0.2302   0.6688   0.0603
  -2.000   0.8865   0.01710   0.01124  -0.2302   0.6654   0.0627
  -1.750   0.9156   0.01608   0.00990  -0.2309   0.6618   0.0679
  -1.500   0.9419   0.01612   0.01002  -0.2309   0.6583   0.0699
  -1.250   0.9709   0.01573   0.00942  -0.2314   0.6550   0.0736
  -1.000   0.9992   0.01523   0.00876  -0.2320   0.6516   0.0781
  -0.750   1.0245   0.01524   0.00886  -0.2318   0.6480   0.0816
  -0.500   1.0519   0.01491   0.00839  -0.2319   0.6443   0.0843
  -0.250   1.0729   0.01655   0.01043  -0.2314   0.6403   0.1152
   0.000   1.0995   0.01640   0.01026  -0.2316   0.6361   0.1191
   0.250   1.1324   0.01380   0.00696  -0.2322   0.6317   0.0906
   0.500   1.1582   0.01352   0.00661  -0.2320   0.6270   0.0909
   0.750   1.1854   0.01338   0.00638  -0.2320   0.6230   0.0920
   1.000   1.2123   0.01327   0.00622  -0.2321   0.6195   0.0928
   1.250   1.2374   0.01313   0.00608  -0.2318   0.6157   0.0930
   1.500   1.2629   0.01303   0.00596  -0.2315   0.6118   0.0933
   1.750   1.2892   0.01298   0.00586  -0.2314   0.6081   0.0938
   2.000   1.3165   0.01299   0.00582  -0.2316   0.6046   0.0945
   2.250   1.3404   0.01297   0.00584  -0.2311   0.6010   0.0957
   2.500   1.3649   0.01297   0.00586  -0.2306   0.5971   0.0965
   2.750   1.3899   0.01299   0.00587  -0.2303   0.5933   0.0970
   3.000   1.4167   0.01307   0.00590  -0.2304   0.5895   0.0976
   3.250   1.4391   0.01312   0.00601  -0.2296   0.5856   0.0982
   3.500   1.4614   0.01319   0.00611  -0.2288   0.5810   0.0987
   3.750   1.4845   0.01326   0.00617  -0.2281   0.5763   0.0999
   4.000   1.5075   0.01338   0.00629  -0.2275   0.5717   0.1015
   4.250   1.5259   0.01348   0.00645  -0.2259   0.5666   0.1040
   4.500   1.5448   0.01362   0.00661  -0.2244   0.5620   0.1071
   4.750   1.5673   0.01381   0.00677  -0.2237   0.5578   0.1105
   5.000   1.5865   0.01399   0.00704  -0.2224   0.5535   0.1175
   5.250   1.6065   0.01417   0.00735  -0.2213   0.5488   0.1658
   5.500   1.6272   0.01437   0.00766  -0.2204   0.5442   0.2369
   5.750   1.6470   0.01380   0.00815  -0.2195   0.5397   1.0000
   6.000   1.6645   0.01411   0.00848  -0.2179   0.5345   1.0000
   6.250   1.6813   0.01447   0.00880  -0.2163   0.5286   1.0000
   6.500   1.6969   0.01487   0.00921  -0.2144   0.5219   1.0000
   6.750   1.7105   0.01534   0.00968  -0.2123   0.5139   1.0000
   7.000   1.7246   0.01586   0.01018  -0.2104   0.5065   1.0000
   7.250   1.7379   0.01642   0.01074  -0.2084   0.4983   1.0000
   7.500   1.7511   0.01704   0.01135  -0.2064   0.4908   1.0000
   7.750   1.7636   0.01771   0.01203  -0.2044   0.4822   1.0000
   8.000   1.7740   0.01852   0.01283  -0.2021   0.4724   1.0000
   8.500   1.7922   0.02040   0.01469  -0.1974   0.4515   1.0000
   8.750   1.8002   0.02148   0.01575  -0.1950   0.4410   1.0000
   9.000   1.8049   0.02279   0.01702  -0.1923   0.4294   1.0000
   9.250   1.8087   0.02422   0.01842  -0.1895   0.4163   1.0000
   9.500   1.8111   0.02582   0.01999  -0.1867   0.4018   1.0000
   9.750   1.8117   0.02763   0.02175  -0.1838   0.3869   1.0000
  10.000   1.8099   0.02968   0.02376  -0.1808   0.3713   1.0000
  10.250   1.8070   0.03191   0.02593  -0.1778   0.3554   1.0000
  10.500   1.8040   0.03423   0.02820  -0.1749   0.3401   1.0000
  10.750   1.7991   0.03679   0.03070  -0.1720   0.3240   1.0000
  11.000   1.7916   0.03966   0.03350  -0.1690   0.3065   1.0000
  11.250   1.7835   0.04268   0.03644  -0.1661   0.2866   1.0000
  11.500   1.7696   0.04632   0.03995  -0.1628   0.2610   1.0000
  11.750   1.7479   0.05083   0.04428  -0.1592   0.2260   1.0000
  12.000   1.7180   0.05630   0.04952  -0.1552   0.1852   1.0000
  12.250   1.6945   0.06127   0.05435  -0.1520   0.1596   1.0000
  12.500   1.6815   0.06532   0.05834  -0.1496   0.1412   1.0000
  12.750   1.6657   0.06978   0.06268  -0.1473   0.1161   1.0000
  13.000   1.6353   0.07598   0.06865  -0.1445   0.0759   1.0000
  13.250   1.6073   0.08217   0.07470  -0.1421   0.0398   1.0000
  13.500   1.5924   0.08693   0.07943  -0.1406   0.0224   1.0000
  13.750   1.5910   0.09011   0.08268  -0.1396   0.0202   1.0000
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