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GOE 410 AIRFOIL (goe410-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 410 AIRFOIL (goe410-il)
Reynolds number: 50,000
Max Cl/Cd: 25.16 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe410-il-50000-n5.txt
Download as CSV file: xf-goe410-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 410 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6540   0.12458   0.11571   0.0045   1.0000   0.1383
 -13.000  -0.6593   0.11919   0.11031   0.0020   1.0000   0.1417
 -12.500  -0.9275   0.06803   0.05861  -0.0297   1.0000   0.1470
 -12.250  -0.8655   0.07144   0.06225  -0.0260   1.0000   0.1512
 -12.000  -0.9054   0.06393   0.05455  -0.0293   1.0000   0.1528
 -11.750  -0.9289   0.05900   0.04943  -0.0305   1.0000   0.1546
 -11.500  -0.9472   0.05506   0.04529  -0.0305   1.0000   0.1566
 -11.250  -0.9622   0.05185   0.04185  -0.0295   1.0000   0.1587
 -11.000  -0.9754   0.04913   0.03886  -0.0275   1.0000   0.1610
 -10.750  -0.9752   0.04681   0.03632  -0.0261   1.0000   0.1636
 -10.500  -0.9496   0.04554   0.03515  -0.0259   1.0000   0.1671
 -10.250  -0.9351   0.04394   0.03349  -0.0250   1.0000   0.1704
 -10.000  -0.9243   0.04222   0.03161  -0.0240   1.0000   0.1740
  -9.750  -0.9156   0.04043   0.02958  -0.0228   1.0000   0.1778
  -9.500  -0.8942   0.03916   0.02835  -0.0222   1.0000   0.1817
  -9.250  -0.8738   0.03801   0.02724  -0.0215   1.0000   0.1860
  -9.000  -0.8569   0.03671   0.02586  -0.0206   1.0000   0.1905
  -8.750  -0.8405   0.03541   0.02444  -0.0197   1.0000   0.1954
  -8.500  -0.8198   0.03447   0.02363  -0.0188   1.0000   0.2006
  -8.250  -0.8024   0.03340   0.02254  -0.0178   1.0000   0.2069
  -8.000  -0.7845   0.03238   0.02154  -0.0168   1.0000   0.2131
  -7.750  -0.7666   0.03146   0.02070  -0.0157   1.0000   0.2199
  -7.500  -0.7497   0.03050   0.01977  -0.0145   1.0000   0.2282
  -7.250  -0.7331   0.02966   0.01904  -0.0132   1.0000   0.2375
  -7.000  -0.7170   0.02883   0.01833  -0.0118   1.0000   0.2481
  -6.750  -0.7011   0.02803   0.01762  -0.0104   1.0000   0.2610
  -6.500  -0.6859   0.02730   0.01704  -0.0088   1.0000   0.2765
  -6.250  -0.6712   0.02668   0.01658  -0.0070   1.0000   0.2942
  -6.000  -0.6572   0.02618   0.01627  -0.0051   1.0000   0.3139
  -5.750  -0.6443   0.02581   0.01606  -0.0029   1.0000   0.3352
  -5.500  -0.6329   0.02555   0.01592  -0.0005   1.0000   0.3567
  -5.250  -0.6240   0.02538   0.01582   0.0021   1.0000   0.3767
  -5.000  -0.5912   0.02535   0.01582   0.0006   0.9819   0.4016
  -4.750  -0.5478   0.02543   0.01590  -0.0024   0.9594   0.4254
  -4.500  -0.5047   0.02545   0.01586  -0.0053   0.9380   0.4469
  -4.250  -0.4633   0.02544   0.01580  -0.0077   0.9171   0.4647
  -4.000  -0.4263   0.02539   0.01569  -0.0091   0.8948   0.4803
  -3.750  -0.3922   0.02529   0.01548  -0.0100   0.8732   0.4954
  -3.500  -0.3614   0.02522   0.01531  -0.0102   0.8528   0.5108
  -3.250  -0.3309   0.02538   0.01548  -0.0097   0.8334   0.5241
  -3.000  -0.3039   0.02540   0.01545  -0.0089   0.8149   0.5376
  -2.750  -0.2795   0.02533   0.01527  -0.0080   0.7975   0.5519
  -2.500  -0.2527   0.02544   0.01538  -0.0069   0.7814   0.5631
  -2.250  -0.2281   0.02537   0.01523  -0.0059   0.7664   0.5748
  -2.000  -0.2037   0.02532   0.01514  -0.0049   0.7509   0.5853
  -1.750  -0.1790   0.02521   0.01499  -0.0041   0.7367   0.5946
  -1.500  -0.1533   0.02512   0.01482  -0.0034   0.7243   0.6033
  -1.250  -0.1287   0.02496   0.01460  -0.0028   0.7116   0.6122
  -1.000  -0.1028   0.02492   0.01456  -0.0021   0.6994   0.6202
  -0.750  -0.0777   0.02476   0.01430  -0.0016   0.6892   0.6302
  -0.500  -0.0517   0.02479   0.01438  -0.0010   0.6774   0.6380
   0.000   0.0000   0.02474   0.01430   0.0000   0.6570   0.6570
   0.500   0.0517   0.02479   0.01438   0.0010   0.6380   0.6774
   0.750   0.0777   0.02476   0.01429   0.0016   0.6302   0.6891
   1.000   0.1028   0.02492   0.01456   0.0021   0.6202   0.6994
   1.250   0.1287   0.02496   0.01460   0.0028   0.6122   0.7117
   1.500   0.1534   0.02511   0.01482   0.0034   0.6033   0.7243
   1.750   0.1790   0.02521   0.01499   0.0041   0.5945   0.7367
   2.000   0.2037   0.02532   0.01514   0.0049   0.5853   0.7509
   2.250   0.2281   0.02536   0.01523   0.0059   0.5748   0.7664
   2.500   0.2527   0.02544   0.01538   0.0069   0.5630   0.7814
   2.750   0.2795   0.02533   0.01527   0.0080   0.5520   0.7976
   3.000   0.3039   0.02540   0.01545   0.0089   0.5376   0.8149
   3.250   0.3309   0.02537   0.01548   0.0097   0.5241   0.8334
   3.500   0.3614   0.02522   0.01531   0.0102   0.5108   0.8528
   3.750   0.3922   0.02528   0.01548   0.0100   0.4954   0.8732
   4.000   0.4263   0.02539   0.01569   0.0091   0.4804   0.8948
   4.250   0.4633   0.02544   0.01580   0.0076   0.4647   0.9172
   4.500   0.5047   0.02545   0.01586   0.0053   0.4468   0.9380
   4.750   0.5478   0.02543   0.01590   0.0024   0.4254   0.9594
   5.000   0.5913   0.02534   0.01581  -0.0006   0.4016   0.9819
   5.250   0.6239   0.02537   0.01582  -0.0021   0.3767   1.0000
   5.500   0.6329   0.02555   0.01591   0.0005   0.3568   1.0000
   5.750   0.6442   0.02581   0.01606   0.0029   0.3352   1.0000
   6.000   0.6571   0.02618   0.01627   0.0051   0.3139   1.0000
   6.250   0.6712   0.02668   0.01658   0.0070   0.2943   1.0000
   6.500   0.6859   0.02730   0.01703   0.0088   0.2765   1.0000
   6.750   0.7011   0.02803   0.01762   0.0103   0.2610   1.0000
   7.000   0.7170   0.02883   0.01833   0.0118   0.2481   1.0000
   7.250   0.7332   0.02966   0.01903   0.0132   0.2376   1.0000
   7.500   0.7498   0.03050   0.01977   0.0145   0.2282   1.0000
   7.750   0.7668   0.03146   0.02070   0.0156   0.2200   1.0000
   8.000   0.7846   0.03238   0.02154   0.0168   0.2131   1.0000
   8.250   0.8026   0.03340   0.02254   0.0178   0.2069   1.0000
   8.500   0.8200   0.03446   0.02362   0.0188   0.2006   1.0000
   8.750   0.8407   0.03541   0.02443   0.0196   0.1954   1.0000
   9.000   0.8571   0.03671   0.02586   0.0206   0.1905   1.0000
   9.250   0.8741   0.03801   0.02724   0.0215   0.1860   1.0000
   9.500   0.8945   0.03916   0.02835   0.0222   0.1817   1.0000
   9.750   0.9157   0.04043   0.02958   0.0227   0.1778   1.0000
  10.000   0.9245   0.04222   0.03161   0.0240   0.1740   1.0000
  10.250   0.9354   0.04394   0.03349   0.0250   0.1704   1.0000
  10.500   0.9500   0.04553   0.03513   0.0258   0.1671   1.0000
  10.750   0.9759   0.04680   0.03630   0.0260   0.1636   1.0000
  11.000   0.9757   0.04913   0.03886   0.0274   0.1610   1.0000
  11.250   0.9630   0.05184   0.04184   0.0294   0.1588   1.0000
  11.500   0.9478   0.05506   0.04529   0.0305   0.1565   1.0000
  11.750   0.9298   0.05898   0.04941   0.0305   0.1546   1.0000
  12.000   0.9073   0.06382   0.05443   0.0293   0.1527   1.0000
  12.250   0.8824   0.06955   0.06031   0.0272   0.1508   1.0000
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