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GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 430 AIRFOIL (goe430-il)
Reynolds number: 100,000
Max Cl/Cd: 59.74 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe430-il-100000.txt
Download as CSV file: xf-goe430-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 430 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3452   0.10980   0.10490  -0.0278   1.0000   0.1603
  -8.250  -0.3957   0.11099   0.10626  -0.0268   1.0000   0.1630
  -8.000  -0.4448   0.11173   0.10716  -0.0246   1.0000   0.1635
  -7.750  -0.4024   0.10531   0.10066  -0.0230   1.0000   0.1653
  -7.500  -0.3832   0.10275   0.09809  -0.0205   1.0000   0.1681
  -7.250  -0.3863   0.10130   0.09669  -0.0182   1.0000   0.1711
  -7.000  -0.4005   0.10017   0.09563  -0.0159   1.0000   0.1743
  -6.250  -0.3977   0.05908   0.05394  -0.0775   0.9779   0.1325
  -6.000  -0.3614   0.05226   0.04683  -0.0866   0.9724   0.1302
  -5.750  -0.3102   0.04338   0.03726  -0.1008   0.9693   0.1282
  -5.500  -0.2641   0.03790   0.03096  -0.1097   0.9634   0.1298
  -5.250  -0.2132   0.03473   0.02724  -0.1167   0.9578   0.1337
  -5.000  -0.1701   0.03329   0.02568  -0.1205   0.9499   0.1374
  -4.750  -0.1203   0.03155   0.02357  -0.1255   0.9426   0.1427
  -4.500  -0.0748   0.03001   0.02168  -0.1296   0.9352   0.1499
  -4.250  -0.0336   0.02915   0.02076  -0.1325   0.9277   0.1590
  -4.000   0.0161   0.02795   0.01946  -0.1369   0.9239   0.1714
  -3.750   0.0458   0.02728   0.01876  -0.1377   0.9141   0.1858
  -3.500   0.0918   0.02670   0.01816  -0.1412   0.9090   0.2100
  -3.250   0.1233   0.02653   0.01793  -0.1421   0.8998   0.2289
  -3.000   0.1649   0.02621   0.01768  -0.1446   0.8936   0.2471
  -2.750   0.2017   0.02606   0.01752  -0.1462   0.8863   0.2639
  -2.500   0.2378   0.02586   0.01734  -0.1476   0.8781   0.2812
  -2.250   0.2860   0.02543   0.01701  -0.1510   0.8745   0.3036
  -2.000   0.3107   0.02536   0.01696  -0.1505   0.8631   0.3189
  -1.750   0.3556   0.02470   0.01636  -0.1532   0.8590   0.3391
  -1.500   0.3836   0.02448   0.01620  -0.1531   0.8488   0.3574
  -1.250   0.4240   0.02386   0.01567  -0.1548   0.8432   0.3863
  -1.000   0.4542   0.02364   0.01556  -0.1548   0.8341   0.4184
  -0.750   0.4896   0.02322   0.01527  -0.1554   0.8270   0.4538
  -0.500   0.5199   0.02301   0.01514  -0.1552   0.8182   0.4856
  -0.250   0.5526   0.02265   0.01488  -0.1552   0.8104   0.5164
   0.000   0.5812   0.02248   0.01481  -0.1547   0.8013   0.5453
   0.250   0.6134   0.02214   0.01454  -0.1547   0.7937   0.5760
   0.500   0.6400   0.02207   0.01455  -0.1538   0.7837   0.6040
   0.750   0.6726   0.02165   0.01418  -0.1536   0.7766   0.6343
   1.000   0.6977   0.02157   0.01417  -0.1525   0.7655   0.6650
   1.250   0.7310   0.02092   0.01356  -0.1522   0.7590   0.7017
   1.500   0.7539   0.02075   0.01346  -0.1506   0.7466   0.7363
   1.750   0.7803   0.02026   0.01304  -0.1493   0.7370   0.7757
   2.000   0.8047   0.01969   0.01257  -0.1474   0.7276   0.8210
   2.250   0.8201   0.01933   0.01243  -0.1441   0.7165   0.9001
   2.500   0.8628   0.01896   0.01191  -0.1467   0.7091   1.0000
   2.750   0.8928   0.01933   0.01219  -0.1476   0.6973   1.0000
   3.000   0.9255   0.01945   0.01220  -0.1485   0.6882   1.0000
   3.250   0.9572   0.01955   0.01218  -0.1490   0.6787   1.0000
   3.500   0.9849   0.01989   0.01246  -0.1490   0.6685   1.0000
   3.750   1.0175   0.01995   0.01242  -0.1495   0.6607   1.0000
   4.000   1.0424   0.02042   0.01290  -0.1491   0.6506   1.0000
   4.250   1.0747   0.02053   0.01291  -0.1495   0.6436   1.0000
   4.500   1.0980   0.02109   0.01352  -0.1489   0.6338   1.0000
   4.750   1.1304   0.02110   0.01342  -0.1491   0.6256   1.0000
   5.000   1.1532   0.02153   0.01390  -0.1482   0.6143   1.0000
   5.250   1.1798   0.02175   0.01411  -0.1477   0.6037   1.0000
   5.500   1.2093   0.02181   0.01411  -0.1475   0.5937   1.0000
   5.750   1.2316   0.02221   0.01458  -0.1464   0.5822   1.0000
   6.000   1.2581   0.02238   0.01475  -0.1458   0.5713   1.0000
   6.250   1.2857   0.02247   0.01479  -0.1453   0.5601   1.0000
   6.500   1.3069   0.02281   0.01523  -0.1440   0.5476   1.0000
   6.750   1.3307   0.02304   0.01551  -0.1430   0.5354   1.0000
   7.000   1.3548   0.02316   0.01563  -0.1419   0.5216   1.0000
   7.250   1.3769   0.02328   0.01575  -0.1405   0.5057   1.0000
   7.500   1.3973   0.02346   0.01595  -0.1388   0.4883   1.0000
   7.750   1.4164   0.02371   0.01622  -0.1370   0.4696   1.0000
   8.000   1.4345   0.02404   0.01653  -0.1350   0.4494   1.0000
   8.250   1.4523   0.02445   0.01685  -0.1330   0.4281   1.0000
   8.500   1.4647   0.02507   0.01750  -0.1303   0.4043   1.0000
   8.750   1.4766   0.02573   0.01813  -0.1275   0.3808   1.0000
   9.000   1.4873   0.02647   0.01882  -0.1247   0.3585   1.0000
   9.250   1.4963   0.02727   0.01963  -0.1217   0.3374   1.0000
   9.500   1.5034   0.02812   0.02042  -0.1184   0.3193   1.0000
   9.750   1.5101   0.02910   0.02133  -0.1153   0.3028   1.0000
  10.000   1.5166   0.03024   0.02236  -0.1123   0.2872   1.0000
  10.250   1.5233   0.03154   0.02353  -0.1095   0.2720   1.0000
  10.500   1.5307   0.03298   0.02484  -0.1069   0.2571   1.0000
  10.750   1.5390   0.03450   0.02625  -0.1046   0.2427   1.0000
  11.000   1.5477   0.03606   0.02775  -0.1024   0.2292   1.0000
  11.250   1.5585   0.03759   0.02920  -0.1006   0.2173   1.0000
  11.500   1.5707   0.03902   0.03056  -0.0989   0.2066   1.0000
  11.750   1.5747   0.04064   0.03235  -0.0965   0.1978   1.0000
  12.000   1.5892   0.04198   0.03356  -0.0952   0.1891   1.0000
  12.250   1.5869   0.04376   0.03564  -0.0924   0.1823   1.0000
  12.500   1.5922   0.04526   0.03715  -0.0904   0.1752   1.0000
  12.750   1.5895   0.04723   0.03935  -0.0881   0.1684   1.0000
  13.000   1.5872   0.04916   0.04138  -0.0860   0.1617   1.0000
  13.250   1.5840   0.05136   0.04374  -0.0842   0.1552   1.0000
  13.500   1.5795   0.05377   0.04633  -0.0826   0.1484   1.0000
  13.750   1.5742   0.05641   0.04907  -0.0812   0.1417   1.0000
  14.000   1.5656   0.05953   0.05237  -0.0802   0.1340   1.0000
  14.250   1.5559   0.06307   0.05605  -0.0795   0.1255   1.0000
  14.500   1.5438   0.06711   0.06009  -0.0792   0.1165   1.0000
  14.750   1.5295   0.07179   0.06486  -0.0793   0.1061   1.0000
  15.000   1.5146   0.07680   0.06990  -0.0795   0.0954   1.0000
  15.250   1.5009   0.08173   0.07481  -0.0795   0.0858   1.0000
  15.500   1.4908   0.08617   0.07920  -0.0793   0.0783   1.0000
  15.750   1.4843   0.09026   0.08330  -0.0793   0.0725   1.0000
  16.000   1.4804   0.09400   0.08710  -0.0791   0.0680   1.0000
  16.250   1.4767   0.09790   0.09112  -0.0794   0.0642   1.0000
  16.500   1.4771   0.10095   0.09408  -0.0794   0.0611   1.0000
  16.750   1.4733   0.10508   0.09843  -0.0800   0.0587   1.0000
  17.000   1.4702   0.10909   0.10262  -0.0808   0.0563   1.0000
  17.250   1.4693   0.11268   0.10626  -0.0816   0.0543   1.0000
  17.500   1.4767   0.11455   0.10803  -0.0812   0.0524   1.0000
  17.750   1.4728   0.11888   0.11260  -0.0822   0.0513   1.0000
  18.000   1.4676   0.12353   0.11749  -0.0837   0.0503   1.0000
  18.250   1.4610   0.12853   0.12271  -0.0856   0.0495   1.0000
  18.500   1.4526   0.13399   0.12838  -0.0880   0.0489   1.0000
  18.750   1.4412   0.14020   0.13481  -0.0912   0.0484   1.0000
  19.000   1.4248   0.14773   0.14258  -0.0957   0.0481   1.0000
  19.250   1.3950   0.15881   0.15399  -0.1031   0.0485   1.0000
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