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GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 425 AIRFOIL (goe425-il)
Reynolds number: 50,000
Max Cl/Cd: 17.38 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe425-il-50000-n5.txt
Download as CSV file: xf-goe425-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 425 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2857   0.13256   0.12564  -0.0404   1.0000   0.1399
 -11.250  -0.2905   0.12988   0.12305  -0.0429   1.0000   0.1405
 -11.000  -0.2931   0.12689   0.12015  -0.0450   1.0000   0.1408
 -10.000  -0.2852   0.10616   0.09966  -0.0527   0.9944   0.0870
  -9.750  -0.2645   0.10187   0.09535  -0.0565   0.9722   0.0849
  -9.500  -0.2529   0.09672   0.09018  -0.0617   0.9512   0.0824
  -9.250  -0.2650   0.08757   0.08099  -0.0720   0.9303   0.0778
  -9.000  -0.2531   0.08291   0.07628  -0.0763   0.9130   0.0769
  -8.750  -0.2498   0.07724   0.07053  -0.0819   0.8956   0.0761
  -8.500  -0.2578   0.07113   0.06431  -0.0880   0.8781   0.0753
  -8.250  -0.2665   0.06583   0.05880  -0.0921   0.8629   0.0748
  -8.000  -0.2717   0.06120   0.05390  -0.0948   0.8498   0.0746
  -7.750  -0.2725   0.05722   0.04959  -0.0963   0.8376   0.0747
  -7.500  -0.2694   0.05377   0.04579  -0.0969   0.8258   0.0748
  -7.250  -0.2607   0.05051   0.04211  -0.0972   0.8167   0.0748
  -7.000  -0.2506   0.04775   0.03897  -0.0970   0.8059   0.0747
  -6.750  -0.2357   0.04515   0.03594  -0.0967   0.7976   0.0747
  -6.500  -0.2198   0.04298   0.03338  -0.0962   0.7880   0.0749
  -6.250  -0.1999   0.04090   0.03089  -0.0957   0.7808   0.0753
  -6.000  -0.1810   0.03924   0.02889  -0.0951   0.7717   0.0759
  -5.750  -0.1579   0.03761   0.02682  -0.0946   0.7652   0.0773
  -5.500  -0.1368   0.03648   0.02547  -0.0940   0.7566   0.0788
  -5.250  -0.1126   0.03546   0.02432  -0.0935   0.7497   0.0807
  -5.000  -0.0884   0.03449   0.02317  -0.0930   0.7430   0.0823
  -4.750  -0.0642   0.03362   0.02212  -0.0925   0.7356   0.0837
  -4.500  -0.0372   0.03270   0.02099  -0.0921   0.7302   0.0855
  -4.250  -0.0132   0.03209   0.02021  -0.0914   0.7232   0.0874
  -4.000   0.0106   0.03154   0.01964  -0.0908   0.7166   0.0901
  -3.750   0.0370   0.03097   0.01894  -0.0904   0.7118   0.0948
  -3.500   0.0589   0.03070   0.01858  -0.0896   0.7048   0.0996
  -3.250   0.0822   0.03028   0.01814  -0.0890   0.6990   0.1051
  -3.000   0.1084   0.02977   0.01747  -0.0886   0.6945   0.1126
  -2.750   0.1302   0.02946   0.01716  -0.0882   0.6883   0.1237
  -2.500   0.1517   0.02894   0.01679  -0.0877   0.6823   0.1465
  -2.250   0.1747   0.02784   0.01632  -0.0876   0.6780   0.2473
  -2.000   0.1916   0.02735   0.01676  -0.0858   0.6732   0.4663
  -1.750   0.2078   0.02768   0.01730  -0.0838   0.6669   0.5607
  -1.500   0.2271   0.02773   0.01752  -0.0815   0.6622   0.6345
  -1.250   0.2469   0.02758   0.01758  -0.0786   0.6588   0.7100
  -1.000   0.2605   0.02797   0.01824  -0.0756   0.6524   0.7744
  -0.750   0.2888   0.02813   0.01851  -0.0748   0.6473   0.8413
  -0.500   0.3396   0.02817   0.01842  -0.0785   0.6435   0.9036
  -0.250   0.3976   0.02834   0.01836  -0.0845   0.6394   0.9668
   0.000   0.4258   0.02908   0.01894  -0.0867   0.6326   1.0000
   0.250   0.4430   0.02949   0.01912  -0.0858   0.6281   1.0000
   0.500   0.4673   0.02971   0.01910  -0.0854   0.6248   1.0000
   0.750   0.4762   0.03085   0.02013  -0.0838   0.6179   1.0000
   1.000   0.4946   0.03152   0.02065  -0.0829   0.6127   1.0000
   1.250   0.5199   0.03184   0.02079  -0.0827   0.6091   1.0000
   1.500   0.5376   0.03265   0.02148  -0.0818   0.6042   1.0000
   1.750   0.5479   0.03390   0.02267  -0.0803   0.5974   1.0000
   2.000   0.5721   0.03435   0.02298  -0.0799   0.5934   1.0000
   2.250   0.6008   0.03456   0.02304  -0.0799   0.5906   1.0000
   2.500   0.5984   0.03670   0.02520  -0.0776   0.5818   1.0000
   2.750   0.6204   0.03733   0.02574  -0.0771   0.5774   1.0000
   3.000   0.6486   0.03758   0.02588  -0.0770   0.5745   1.0000
   3.500   0.6624   0.04093   0.02920  -0.0740   0.5609   1.0000
   3.750   0.6904   0.04120   0.02940  -0.0739   0.5580   1.0000
   4.250   0.6956   0.04531   0.03350  -0.0707   0.5435   1.0000
   4.500   0.7242   0.04558   0.03372  -0.0706   0.5408   1.0000
   5.500   0.7257   0.05570   0.04388  -0.0660   0.5115   1.0000
   5.750   0.7457   0.05672   0.04490  -0.0656   0.5079   1.0000
   6.000   0.7725   0.05716   0.04533  -0.0653   0.5055   1.0000
   6.250   0.7493   0.06190   0.05011  -0.0641   0.4944   1.0000
   6.500   0.7698   0.06291   0.05113  -0.0637   0.4907   1.0000
   6.750   0.7950   0.06354   0.05178  -0.0634   0.4883   1.0000
   7.000   0.7713   0.06849   0.05679  -0.0625   0.4781   1.0000
   7.250   0.7896   0.06972   0.05804  -0.0621   0.4742   1.0000
   7.500   0.8147   0.07036   0.05871  -0.0618   0.4717   1.0000
   7.750   0.7940   0.07520   0.06360  -0.0612   0.4626   1.0000
   8.000   0.8083   0.07683   0.06529  -0.0608   0.4582   1.0000
   8.250   0.8323   0.07759   0.06610  -0.0605   0.4554   1.0000
   8.750   0.8288   0.08387   0.07250  -0.0598   0.4424   1.0000
   9.000   0.8521   0.08468   0.07338  -0.0594   0.4393   1.0000
   9.250   0.8407   0.08860   0.07737  -0.0591   0.4305   1.0000
   9.500   0.8609   0.08938   0.07821  -0.0585   0.4250   1.0000
  10.000   0.8856   0.09185   0.08082  -0.0571   0.4093   1.0000
  10.500   0.9058   0.09500   0.08414  -0.0560   0.3941   1.0000
  10.750   0.9346   0.09466   0.08389  -0.0552   0.3904   1.0000
  11.000   0.9228   0.09865   0.08797  -0.0551   0.3791   1.0000
  11.250   0.9529   0.09803   0.08748  -0.0542   0.3754   1.0000
  11.500   0.9416   0.10200   0.09154  -0.0542   0.3634   1.0000
  11.750   0.9708   0.10129   0.09094  -0.0532   0.3593   1.0000
  12.000   0.9619   0.10503   0.09478  -0.0533   0.3471   1.0000
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