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GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 421 AIRFOIL (goe421-il)
Reynolds number: 100,000
Max Cl/Cd: 34.33 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe421-il-100000-n5.txt
Download as CSV file: xf-goe421-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 421 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.0863   0.10671   0.10089  -0.1393   0.8945   0.0626
 -11.250   0.0824   0.10377   0.09796  -0.1391   0.8868   0.0630
 -11.000   0.0833   0.09971   0.09389  -0.1412   0.8821   0.0642
 -10.750   0.0811   0.09412   0.08825  -0.1449   0.8789   0.0655
 -10.500   0.0648   0.08970   0.08385  -0.1451   0.8703   0.0660
 -10.250   0.0441   0.08218   0.07633  -0.1487   0.8649   0.0667
  -9.750  -0.2091   0.04838   0.04197  -0.1628   0.8316   0.0668
  -9.500  -0.2173   0.04726   0.04082  -0.1595   0.8224   0.0675
  -9.250  -0.2035   0.04552   0.03898  -0.1599   0.8177   0.0687
  -9.000  -0.1846   0.04276   0.03596  -0.1624   0.8149   0.0703
  -8.750  -0.1903   0.04130   0.03429  -0.1595   0.8062   0.0712
  -8.500  -0.1767   0.03909   0.03174  -0.1598   0.8013   0.0727
  -8.250  -0.1520   0.03669   0.02885  -0.1618   0.7987   0.0749
  -8.000  -0.1197   0.03529   0.02736  -0.1636   0.7970   0.0769
  -7.750  -0.1213   0.03521   0.02726  -0.1593   0.7875   0.0780
  -7.500  -0.0961   0.03419   0.02610  -0.1597   0.7840   0.0802
  -7.250  -0.0656   0.03289   0.02455  -0.1611   0.7818   0.0828
  -7.000  -0.0317   0.03160   0.02298  -0.1629   0.7801   0.0857
  -6.750  -0.0257   0.03158   0.02299  -0.1598   0.7724   0.0875
  -6.500  -0.0036   0.03107   0.02242  -0.1593   0.7676   0.0904
  -6.250   0.0282   0.03018   0.02134  -0.1604   0.7652   0.0942
  -6.000   0.0627   0.02927   0.02031  -0.1620   0.7634   0.0982
  -5.750   0.0990   0.02849   0.01947  -0.1639   0.7619   0.1035
  -5.500   0.0959   0.02903   0.01996  -0.1591   0.7521   0.1063
  -5.250   0.1254   0.02845   0.01934  -0.1598   0.7490   0.1119
  -5.000   0.1600   0.02780   0.01861  -0.1612   0.7468   0.1200
  -4.750   0.1965   0.02722   0.01805  -0.1629   0.7452   0.1298
  -4.500   0.2085   0.02756   0.01840  -0.1607   0.7389   0.1377
  -4.250   0.2259   0.02782   0.01866  -0.1592   0.7329   0.1485
  -4.000   0.2586   0.02765   0.01845  -0.1601   0.7303   0.1639
  -3.750   0.2943   0.02744   0.01812  -0.1614   0.7284   0.1801
  -3.500   0.3322   0.02717   0.01768  -0.1631   0.7269   0.1957
  -3.250   0.3261   0.02843   0.01899  -0.1580   0.7168   0.2009
  -3.000   0.3564   0.02833   0.01873  -0.1585   0.7137   0.2133
  -2.750   0.3907   0.02806   0.01841  -0.1596   0.7116   0.2246
  -2.500   0.4277   0.02768   0.01795  -0.1612   0.7100   0.2356
  -2.250   0.4266   0.02891   0.01920  -0.1570   0.7008   0.2412
  -2.000   0.4541   0.02890   0.01905  -0.1571   0.6971   0.2508
  -1.750   0.4883   0.02853   0.01871  -0.1581   0.6947   0.2596
  -1.250   0.5295   0.02894   0.01902  -0.1562   0.6831   0.2734
  -1.000   0.5639   0.02838   0.01841  -0.1570   0.6788   0.2823
  -0.750   0.6083   0.02736   0.01726  -0.1593   0.6758   0.2908
  -0.500   0.6161   0.02800   0.01793  -0.1563   0.6666   0.2943
  -0.250   0.6458   0.02768   0.01755  -0.1565   0.6615   0.2992
   0.000   0.6841   0.02710   0.01686  -0.1581   0.6587   0.3052
   0.250   0.7202   0.02666   0.01638  -0.1594   0.6557   0.3111
   0.500   0.7139   0.02805   0.01786  -0.1545   0.6459   0.3141
   0.750   0.7480   0.02766   0.01742  -0.1554   0.6425   0.3208
   1.000   0.7880   0.02704   0.01674  -0.1573   0.6400   0.3283
   1.250   0.7817   0.02848   0.01829  -0.1525   0.6301   0.3321
   1.500   0.8123   0.02823   0.01800  -0.1529   0.6259   0.3416
   1.750   0.8519   0.02758   0.01733  -0.1546   0.6229   0.3542
   2.000   0.8477   0.02901   0.01883  -0.1502   0.6130   0.3625
   2.250   0.8778   0.02878   0.01860  -0.1505   0.6084   0.3792
   2.500   0.9171   0.02812   0.01794  -0.1522   0.6052   0.4018
   2.750   0.9106   0.02971   0.01964  -0.1477   0.5949   0.4150
   3.000   0.9418   0.02938   0.01937  -0.1482   0.5903   0.4438
   3.250   0.9775   0.02881   0.01887  -0.1493   0.5864   0.4854
   3.500   0.9723   0.03033   0.02060  -0.1451   0.5756   0.5183
   3.750   0.9984   0.02908   0.02014  -0.1439   0.5713   0.8055
   4.000   0.9934   0.03041   0.02152  -0.1398   0.5605   1.0000
   4.250   1.0230   0.03024   0.02121  -0.1400   0.5548   1.0000
   4.500   1.0289   0.03146   0.02240  -0.1375   0.5449   1.0000
   4.750   1.0532   0.03157   0.02241  -0.1371   0.5381   1.0000
   5.000   1.0639   0.03254   0.02335  -0.1352   0.5289   1.0000
   5.250   1.0848   0.03288   0.02362  -0.1345   0.5214   1.0000
   5.500   1.0990   0.03368   0.02437  -0.1331   0.5128   1.0000
   5.750   1.1175   0.03419   0.02481  -0.1321   0.5047   1.0000
   6.000   1.1347   0.03481   0.02539  -0.1311   0.4966   1.0000
   6.250   1.1510   0.03549   0.02602  -0.1299   0.4883   1.0000
   6.500   1.1723   0.03584   0.02629  -0.1293   0.4813   1.0000
   6.750   1.1846   0.03685   0.02728  -0.1279   0.4726   1.0000
   7.000   1.2138   0.03664   0.02694  -0.1280   0.4672   1.0000
   7.250   1.2185   0.03825   0.02858  -0.1259   0.4579   1.0000
   7.500   1.2432   0.03837   0.02861  -0.1256   0.4522   1.0000
   7.750   1.2554   0.03947   0.02971  -0.1243   0.4451   1.0000
   8.000   1.2712   0.04030   0.03051  -0.1233   0.4388   1.0000
   8.250   1.2981   0.04030   0.03041  -0.1233   0.4345   1.0000
   8.500   1.3075   0.04170   0.03186  -0.1219   0.4285   1.0000
   8.750   1.3219   0.04271   0.03288  -0.1209   0.4234   1.0000
   9.000   1.3448   0.04306   0.03319  -0.1206   0.4196   1.0000
   9.250   1.3713   0.04317   0.03324  -0.1206   0.4164   1.0000
   9.500   1.3754   0.04504   0.03521  -0.1189   0.4114   1.0000
   9.750   1.3887   0.04620   0.03641  -0.1179   0.4074   1.0000
  10.000   1.4079   0.04689   0.03710  -0.1174   0.4041   1.0000
  10.250   1.4339   0.04704   0.03723  -0.1174   0.4015   1.0000
  10.500   1.4472   0.04820   0.03843  -0.1164   0.3978   1.0000
  10.750   1.4456   0.05058   0.04093  -0.1144   0.3928   1.0000
  11.000   1.4574   0.05181   0.04220  -0.1134   0.3885   1.0000
  11.250   1.4803   0.05209   0.04246  -0.1132   0.3849   1.0000
  11.500   1.4970   0.05294   0.04333  -0.1125   0.3815   1.0000
  11.750   1.4858   0.05629   0.04686  -0.1101   0.3771   1.0000
  12.000   1.4885   0.05848   0.04916  -0.1087   0.3734   1.0000
  12.250   1.5020   0.05964   0.05039  -0.1080   0.3703   1.0000
  12.500   1.5265   0.05975   0.05049  -0.1079   0.3676   1.0000
  12.750   1.5438   0.06056   0.05133  -0.1074   0.3647   1.0000
  13.000   1.5011   0.06734   0.05841  -0.1039   0.3596   1.0000
  13.250   1.4866   0.07157   0.06280  -0.1022   0.3555   1.0000
  13.500   1.4982   0.07298   0.06429  -0.1016   0.3526   1.0000
  13.750   1.5266   0.07249   0.06381  -0.1016   0.3503   1.0000
  14.000   1.5650   0.07098   0.06227  -0.1020   0.3483   1.0000
  14.250   1.3763   0.09692   0.08877  -0.0970   0.3339   1.0000
  14.500   1.4184   0.09411   0.08599  -0.0968   0.3329   1.0000
  14.750   1.4634   0.09107   0.08294  -0.0968   0.3319   1.0000
  15.000   1.5071   0.08837   0.08026  -0.0968   0.3308   1.0000
  15.250   1.3390   0.11463   0.10686  -0.0966   0.3120   1.0000
  15.500   1.3882   0.11032   0.10258  -0.0958   0.3129   1.0000
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