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GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 368 AIRFOIL (goe368-il)
Reynolds number: 50,000
Max Cl/Cd: 29.27 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe368-il-50000.txt
Download as CSV file: xf-goe368-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 368 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4405   0.13066   0.12378   0.0076   1.0000   0.1417
  -9.750  -0.4426   0.12937   0.12257   0.0054   1.0000   0.1448
  -9.500  -0.4529   0.12985   0.12317   0.0023   1.0000   0.1458
  -9.250  -0.4269   0.12118   0.11447   0.0041   1.0000   0.1492
  -9.000  -0.4185   0.11758   0.11089   0.0036   1.0000   0.1532
  -8.750  -0.4169   0.11529   0.10868   0.0021   1.0000   0.1573
  -8.500  -0.4261   0.11509   0.10860  -0.0007   1.0000   0.1593
  -8.250  -0.4132   0.10954   0.10310  -0.0006   1.0000   0.1615
  -8.000  -0.4000   0.10511   0.09868  -0.0002   1.0000   0.1657
  -7.750  -0.3980   0.10263   0.09627  -0.0013   1.0000   0.1705
  -7.500  -0.4087   0.10203   0.09583  -0.0038   1.0000   0.1731
  -7.250  -0.3935   0.09660   0.09043  -0.0029   1.0000   0.1771
  -7.000  -0.3873   0.09349   0.08738  -0.0030   1.0000   0.1828
  -6.750  -0.3936   0.09243   0.08645  -0.0081   1.0000   0.1873
  -6.500  -0.3812   0.08751   0.08154  -0.0067   1.0000   0.1907
  -6.250  -0.3721   0.08410   0.07818  -0.0071   1.0000   0.1964
  -6.000  -0.3706   0.08240   0.07655  -0.0141   1.0000   0.2020
  -5.750  -0.3576   0.07752   0.07174  -0.0114   1.0000   0.2052
  -5.500  -0.3472   0.07430   0.06855  -0.0129   1.0000   0.2119
  -5.250  -0.3369   0.07095   0.06522  -0.0164   1.0000   0.2173
  -5.000  -0.3243   0.06727   0.06159  -0.0160   1.0000   0.2225
  -4.750  -0.3097   0.06408   0.05836  -0.0203   1.0000   0.2306
  -4.500  -0.2959   0.06035   0.05468  -0.0198   1.0000   0.2352
  -4.250  -0.2470   0.04998   0.04359  -0.0357   1.0000   0.1285
  -4.000  -0.2242   0.04557   0.03898  -0.0377   1.0000   0.1250
  -3.750  -0.1988   0.04100   0.03407  -0.0400   1.0000   0.1229
  -3.500  -0.1728   0.03661   0.02925  -0.0416   1.0000   0.1222
  -3.250  -0.1480   0.03321   0.02548  -0.0420   1.0000   0.1255
  -3.000  -0.1223   0.03001   0.02173  -0.0423   1.0000   0.1347
  -2.750  -0.1003   0.02868   0.02018  -0.0414   1.0000   0.1579
  -2.500  -0.0786   0.02677   0.01807  -0.0402   1.0000   0.2031
  -2.250  -0.0651   0.02578   0.01721  -0.0382   1.0000   0.2759
  -2.000  -0.0553   0.02539   0.01701  -0.0358   1.0000   0.3424
  -1.750  -0.0355   0.02465   0.01598  -0.0353   1.0000   0.3543
  -1.500  -0.0153   0.02408   0.01514  -0.0350   1.0000   0.3573
  -1.250   0.0032   0.02373   0.01462  -0.0346   1.0000   0.3626
  -1.000   0.0222   0.02361   0.01428  -0.0345   1.0000   0.3663
  -0.750   0.0405   0.02364   0.01410  -0.0344   1.0000   0.3684
  -0.500   0.0884   0.02363   0.01386  -0.0397   0.9858   0.3736
  -0.250   0.1652   0.02335   0.01333  -0.0494   0.9570   0.3876
   0.000   0.2404   0.02271   0.01264  -0.0581   0.9275   0.4105
   0.250   0.3115   0.02168   0.01178  -0.0651   0.8974   0.4414
   0.500   0.3646   0.02023   0.01105  -0.0684   0.8657   0.5221
   0.750   0.4287   0.01889   0.01025  -0.0720   0.8304   1.0000
   1.000   0.4605   0.01912   0.01006  -0.0707   0.7933   1.0000
   1.250   0.4872   0.01941   0.01000  -0.0686   0.7587   1.0000
   1.500   0.5104   0.01979   0.01012  -0.0664   0.7237   1.0000
   1.750   0.5340   0.02012   0.01020  -0.0642   0.6918   1.0000
   2.000   0.5577   0.02049   0.01032  -0.0622   0.6619   1.0000
   2.250   0.5813   0.02096   0.01057  -0.0604   0.6332   1.0000
   2.500   0.6047   0.02152   0.01094  -0.0588   0.6051   1.0000
   2.750   0.6282   0.02214   0.01144  -0.0573   0.5781   1.0000
   3.000   0.6518   0.02278   0.01195  -0.0560   0.5528   1.0000
   3.250   0.6761   0.02334   0.01234  -0.0547   0.5306   1.0000
   3.500   0.6998   0.02407   0.01304  -0.0537   0.5082   1.0000
   3.750   0.7247   0.02476   0.01361  -0.0527   0.4904   1.0000
   4.000   0.7489   0.02561   0.01448  -0.0519   0.4733   1.0000
   4.250   0.7729   0.02657   0.01545  -0.0512   0.4573   1.0000
   4.500   0.7971   0.02758   0.01648  -0.0505   0.4436   1.0000
   4.750   0.8222   0.02860   0.01746  -0.0498   0.4329   1.0000
   5.000   0.8446   0.03010   0.01926  -0.0496   0.4223   1.0000
   5.250   0.8669   0.03166   0.02101  -0.0492   0.4132   1.0000
   5.500   0.8916   0.03284   0.02223  -0.0486   0.4054   1.0000
   5.750   0.9103   0.03492   0.02467  -0.0485   0.3970   1.0000
   6.000   0.9344   0.03631   0.02615  -0.0480   0.3912   1.0000
   6.250   0.9498   0.03915   0.02947  -0.0482   0.3861   1.0000
   6.500   0.9653   0.04198   0.03264  -0.0483   0.3817   1.0000
   6.750   0.9868   0.04381   0.03464  -0.0479   0.3772   1.0000
   7.000   1.0112   0.04366   0.03451  -0.0460   0.3613   1.0000
   7.250   1.0301   0.04414   0.03516  -0.0445   0.3452   1.0000
   7.500   1.0520   0.04418   0.03539  -0.0428   0.3299   1.0000
   7.750   0.9132   0.07348   0.06518  -0.0603   0.3824   1.0000
   8.000   0.8689   0.08386   0.07534  -0.0666   0.4064   1.0000
   8.250   0.9578   0.07408   0.06613  -0.0553   0.3518   1.0000
   8.500   0.9629   0.07610   0.06826  -0.0541   0.3388   1.0000
   8.750   0.9579   0.08080   0.07300  -0.0553   0.3360   1.0000
   9.000   0.9527   0.08580   0.07805  -0.0568   0.3348   1.0000
   9.250   0.9467   0.09099   0.08330  -0.0585   0.3341   1.0000
   9.500   0.9391   0.09627   0.08860  -0.0603   0.3335   1.0000
   9.750   0.9294   0.10168   0.09404  -0.0624   0.3334   1.0000
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