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GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 431 AIRFOIL (goe431-il)
Reynolds number: 100,000
Max Cl/Cd: 62.74 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe431-il-100000.txt
Download as CSV file: xf-goe431-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 431 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.4058   0.11662   0.11275  -0.0083   1.0000   0.1230
  -6.250  -0.4293   0.11619   0.11240  -0.0074   1.0000   0.1240
  -6.000  -0.4459   0.11465   0.11094  -0.0158   1.0000   0.1249
  -5.750  -0.4374   0.11001   0.10629  -0.0088   1.0000   0.1259
  -5.500  -0.4308   0.10684   0.10312  -0.0059   1.0000   0.1272
  -5.250  -0.3012   0.03827   0.03253  -0.1085   1.0000   0.0672
  -5.000  -0.2672   0.03599   0.02998  -0.1120   1.0000   0.0716
  -4.750  -0.2267   0.03313   0.02648  -0.1169   1.0000   0.0784
  -4.500  -0.1979   0.03223   0.02555  -0.1180   1.0000   0.0856
  -4.250  -0.1720   0.03208   0.02544  -0.1183   1.0000   0.0967
  -4.000  -0.1477   0.03244   0.02575  -0.1180   1.0000   0.1126
  -3.750  -0.1319   0.03405   0.02756  -0.1156   1.0000   0.1273
  -3.500  -0.1172   0.03574   0.02944  -0.1129   1.0000   0.1438
  -3.250  -0.0989   0.03704   0.03070  -0.1113   1.0000   0.1670
  -3.000  -0.0822   0.03818   0.03190  -0.1096   1.0000   0.1864
  -2.750   0.0696   0.04424   0.03805  -0.1263   0.9289   0.2376
  -2.500   0.0964   0.04359   0.03721  -0.1272   0.9199   0.2516
  -2.250   0.1387   0.04371   0.03720  -0.1298   0.9119   0.2675
  -2.000   0.1712   0.04340   0.03670  -0.1314   0.9031   0.2819
  -1.750   0.1981   0.04366   0.03710  -0.1304   0.8949   0.2906
  -1.500   0.2469   0.04210   0.03519  -0.1358   0.8870   0.2907
  -1.250   0.2947   0.04065   0.03337  -0.1407   0.8795   0.2878
  -1.000   0.3396   0.03956   0.03196  -0.1445   0.8717   0.2869
  -0.750   0.3779   0.03892   0.03113  -0.1467   0.8631   0.2887
  -0.500   0.4250   0.03804   0.03002  -0.1501   0.8554   0.2897
  -0.250   0.4588   0.03747   0.02928  -0.1512   0.8456   0.2904
   0.000   0.5096   0.03658   0.02819  -0.1548   0.8392   0.2921
   0.250   0.5396   0.03613   0.02761  -0.1551   0.8284   0.2940
   0.500   0.5934   0.03514   0.02642  -0.1588   0.8230   0.2972
   0.750   0.6215   0.03461   0.02596  -0.1585   0.8112   0.3010
   1.000   0.6779   0.03332   0.02464  -0.1622   0.8067   0.3081
   1.250   0.7077   0.03268   0.02394  -0.1618   0.7941   0.3134
   1.500   0.7667   0.03093   0.02229  -0.1656   0.7904   0.3219
   1.750   0.7974   0.03006   0.02141  -0.1651   0.7774   0.3302
   2.000   0.8319   0.02895   0.02043  -0.1651   0.7653   0.3411
   2.250   0.8928   0.02676   0.01836  -0.1688   0.7609   0.3640
   2.500   0.9294   0.02539   0.01716  -0.1689   0.7470   0.3945
   2.750   0.9693   0.02382   0.01586  -0.1692   0.7319   0.4497
   3.000   1.0119   0.02213   0.01445  -0.1700   0.7142   0.5467
   3.250   1.0330   0.02101   0.01354  -0.1674   0.6841   0.6279
   3.500   1.0514   0.01963   0.01264  -0.1643   0.6471   1.0000
   3.750   1.0991   0.01879   0.01137  -0.1667   0.6106   1.0000
   4.000   1.1441   0.01857   0.01071  -0.1690   0.5804   1.0000
   4.250   1.1803   0.01886   0.01064  -0.1703   0.5591   1.0000
   4.500   1.2145   0.01936   0.01086  -0.1713   0.5438   1.0000
   4.750   1.2504   0.01993   0.01119  -0.1728   0.5321   1.0000
   5.000   1.2794   0.02055   0.01174  -0.1732   0.5218   1.0000
   5.250   1.3121   0.02121   0.01227  -0.1742   0.5133   1.0000
   5.500   1.3411   0.02187   0.01292  -0.1745   0.5056   1.0000
   5.750   1.3750   0.02259   0.01354  -0.1758   0.4997   1.0000
   6.000   1.3993   0.02327   0.01432  -0.1753   0.4933   1.0000
   6.250   1.4296   0.02399   0.01501  -0.1759   0.4866   1.0000
   6.500   1.4538   0.02474   0.01584  -0.1755   0.4799   1.0000
   6.750   1.4784   0.02546   0.01660  -0.1750   0.4726   1.0000
   7.000   1.5059   0.02625   0.01742  -0.1751   0.4663   1.0000
   7.250   1.5258   0.02699   0.01834  -0.1739   0.4601   1.0000
   7.500   1.5542   0.02776   0.01911  -0.1741   0.4538   1.0000
   7.750   1.5737   0.02858   0.02010  -0.1729   0.4476   1.0000
   8.000   1.5953   0.02937   0.02106  -0.1720   0.4416   1.0000
   8.250   1.6265   0.03023   0.02191  -0.1727   0.4360   1.0000
   8.500   1.6385   0.03107   0.02306  -0.1701   0.4294   1.0000
   8.750   1.6656   0.03167   0.02363  -0.1700   0.4195   1.0000
   9.000   1.6745   0.03219   0.02434  -0.1667   0.4080   1.0000
   9.250   1.6852   0.03258   0.02480  -0.1637   0.3944   1.0000
   9.500   1.6963   0.03294   0.02521  -0.1607   0.3815   1.0000
   9.750   1.7094   0.03325   0.02554  -0.1581   0.3692   1.0000
  10.000   1.7206   0.03349   0.02578  -0.1552   0.3566   1.0000
  10.250   1.7164   0.03405   0.02662  -0.1499   0.3461   1.0000
  10.500   1.7151   0.03445   0.02712  -0.1451   0.3349   1.0000
  10.750   1.7121   0.03484   0.02755  -0.1401   0.3228   1.0000
  11.000   1.7023   0.03553   0.02837  -0.1345   0.3103   1.0000
  11.250   1.6906   0.03656   0.02961  -0.1291   0.2971   1.0000
  11.500   1.6792   0.03781   0.03104  -0.1242   0.2813   1.0000
  11.750   1.6657   0.03946   0.03287  -0.1196   0.2586   1.0000
  12.000   1.6478   0.04182   0.03521  -0.1152   0.2102   1.0000
  12.250   1.6216   0.04565   0.03856  -0.1110   0.1675   1.0000
  12.500   1.5955   0.05040   0.04304  -0.1076   0.1344   1.0000
  12.750   1.5718   0.05543   0.04794  -0.1050   0.1051   1.0000
  13.000   1.5501   0.06063   0.05306  -0.1031   0.0881   1.0000
  13.250   1.5306   0.06594   0.05838  -0.1019   0.0788   1.0000
  13.500   1.5108   0.07167   0.06414  -0.1014   0.0738   1.0000
  13.750   1.4950   0.07725   0.06988  -0.1014   0.0694   1.0000
  14.000   1.4789   0.08319   0.07592  -0.1020   0.0664   1.0000
  14.250   1.4627   0.08935   0.08214  -0.1029   0.0640   1.0000
  14.500   1.4551   0.09425   0.08714  -0.1035   0.0610   1.0000
  14.750   1.4511   0.09854   0.09151  -0.1039   0.0579   1.0000
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