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GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 10K AIRFOIL (goe10k-il)
Reynolds number: 500,000
Max Cl/Cd: 74.84 at α=1°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe10k-il-500000-n5.txt
Download as CSV file: xf-goe10k-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 10K AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5344   0.09012   0.08788  -0.0113   1.0000   0.0046
  -7.750  -0.5369   0.08707   0.08485  -0.0107   1.0000   0.0047
  -7.250  -0.5392   0.08079   0.07863  -0.0127   1.0000   0.0048
  -7.000  -0.5348   0.07673   0.07457  -0.0157   1.0000   0.0047
  -6.750  -0.5300   0.07321   0.07106  -0.0175   1.0000   0.0049
  -6.500  -0.5227   0.06922   0.06705  -0.0200   1.0000   0.0049
  -6.250  -0.5137   0.06521   0.06301  -0.0222   1.0000   0.0050
  -6.000  -0.5032   0.06100   0.05874  -0.0243   1.0000   0.0052
  -5.750  -0.4907   0.05681   0.05448  -0.0260   1.0000   0.0052
  -5.500  -0.4769   0.05267   0.05024  -0.0273   1.0000   0.0053
  -5.250  -0.4618   0.04839   0.04585  -0.0282   1.0000   0.0055
  -5.000  -0.4310   0.04306   0.04031  -0.0321   0.9982   0.0056
  -4.500  -0.3690   0.03193   0.02858  -0.0368   0.9942   0.0037
  -4.250  -0.3393   0.02603   0.02223  -0.0373   0.9917   0.0033
  -4.000  -0.3104   0.02211   0.01791  -0.0376   0.9896   0.0035
  -3.750  -0.2808   0.01799   0.01325  -0.0373   0.9881   0.0042
  -3.500  -0.2517   0.01492   0.00962  -0.0369   0.9868   0.0042
  -3.250  -0.2254   0.01287   0.00713  -0.0361   0.9845   0.0042
  -3.000  -0.1977   0.01139   0.00533  -0.0357   0.9825   0.0044
  -2.750  -0.1695   0.01031   0.00408  -0.0357   0.9807   0.0049
  -2.500  -0.1395   0.00977   0.00345  -0.0362   0.9791   0.0063
  -2.250  -0.1090   0.00919   0.00278  -0.0368   0.9779   0.0082
  -2.000  -0.0829   0.00879   0.00231  -0.0364   0.9745   0.0125
  -1.750  -0.0549   0.00835   0.00194  -0.0365   0.9718   0.0430
  -1.500  -0.0250   0.00810   0.00178  -0.0372   0.9697   0.0769
  -1.250   0.0048   0.00767   0.00165  -0.0380   0.9679   0.1707
  -1.000   0.0349   0.00716   0.00154  -0.0389   0.9665   0.3117
  -0.500   0.0841   0.00594   0.00138  -0.0380   0.9563   0.6607
  -0.250   0.1541   0.00517   0.00148  -0.0473   0.9592   0.9873
   0.000   0.1938   0.00513   0.00142  -0.0500   0.9550   1.0000
   0.250   0.2292   0.00502   0.00129  -0.0517   0.9431   1.0000
   0.500   0.2685   0.00494   0.00121  -0.0543   0.9340   1.0000
   0.750   0.3260   0.00476   0.00100  -0.0608   0.9039   1.0000
   1.000   0.3652   0.00488   0.00087  -0.0630   0.8202   1.0000
   1.250   0.3813   0.00539   0.00089  -0.0601   0.6970   1.0000
   1.500   0.3870   0.00667   0.00112  -0.0555   0.4346   1.0000
   1.750   0.4052   0.00735   0.00135  -0.0538   0.3007   1.0000
   2.000   0.4208   0.00844   0.00164  -0.0517   0.0914   1.0000
   2.250   0.4434   0.00882   0.00189  -0.0507   0.0544   1.0000
   2.500   0.4652   0.00935   0.00225  -0.0494   0.0116   1.0000
   2.750   0.4881   0.00979   0.00277  -0.0483   0.0079   1.0000
   3.000   0.5108   0.01026   0.00332  -0.0471   0.0060   1.0000
   3.250   0.5324   0.01094   0.00405  -0.0457   0.0051   1.0000
   3.500   0.5532   0.01185   0.00510  -0.0440   0.0047   1.0000
   3.750   0.5760   0.01244   0.00578  -0.0430   0.0035   1.0000
   4.000   0.5971   0.01375   0.00725  -0.0413   0.0032   1.0000
   4.250   0.6197   0.01558   0.00941  -0.0396   0.0030   1.0000
   4.500   0.6423   0.01797   0.01219  -0.0377   0.0030   1.0000
   4.750   0.6633   0.02087   0.01554  -0.0355   0.0030   1.0000
   5.000   0.6817   0.02392   0.01901  -0.0331   0.0032   1.0000
   5.500   0.7071   0.03375   0.02962  -0.0266   0.0070   1.0000
   5.750   0.7220   0.03757   0.03378  -0.0240   0.0070   1.0000
   6.000   0.7409   0.04240   0.03900  -0.0209   0.0064   1.0000
   6.250   0.7532   0.04673   0.04358  -0.0189   0.0061   1.0000
   6.500   0.7638   0.05102   0.04808  -0.0173   0.0058   1.0000
   6.750   0.7729   0.05526   0.05250  -0.0161   0.0057   1.0000
   7.000   0.7802   0.05954   0.05695  -0.0153   0.0055   1.0000
   7.250   0.7849   0.06338   0.06090  -0.0148   0.0052   1.0000
   7.500   0.7867   0.06676   0.06438  -0.0145   0.0051   1.0000
   7.750   0.7867   0.07383   0.07157  -0.0158   0.0044   1.0000
   8.000   0.7843   0.07852   0.07632  -0.0171   0.0044   1.0000
   8.250   0.7771   0.08249   0.08033  -0.0178   0.0046   1.0000
   8.500   0.7687   0.08616   0.08400  -0.0191   0.0048   1.0000
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