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GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 627 AIRFOIL (goe627-il)
Reynolds number: 50,000
Max Cl/Cd: 29.14 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe627-il-50000-n5.txt
Download as CSV file: xf-goe627-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 627 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3680   0.11091   0.10385  -0.0444   1.0000   0.0730
 -10.500  -0.3706   0.10779   0.10079  -0.0437   1.0000   0.0724
 -10.250  -0.3765   0.10442   0.09748  -0.0434   1.0000   0.0716
 -10.000  -0.3867   0.10062   0.09376  -0.0435   1.0000   0.0710
  -9.750  -0.4010   0.09646   0.08969  -0.0439   1.0000   0.0706
  -9.500  -0.4191   0.09191   0.08522  -0.0446   1.0000   0.0700
  -9.250  -0.4462   0.08647   0.07986  -0.0462   1.0000   0.0690
  -9.000  -0.4816   0.08221   0.07564  -0.0453   1.0000   0.0684
  -8.750  -0.5217   0.07870   0.07214  -0.0419   1.0000   0.0673
  -8.500  -0.5545   0.07484   0.06820  -0.0389   1.0000   0.0668
  -8.250  -0.5817   0.07102   0.06423  -0.0357   1.0000   0.0663
  -8.000  -0.5984   0.06783   0.06089  -0.0327   1.0000   0.0664
  -7.750  -0.6079   0.06469   0.05756  -0.0303   0.9993   0.0669
  -7.500  -0.5963   0.06061   0.05312  -0.0318   0.9916   0.0679
  -7.250  -0.5833   0.05669   0.04877  -0.0328   0.9840   0.0684
  -7.000  -0.5689   0.05321   0.04483  -0.0331   0.9761   0.0688
  -6.750  -0.5497   0.05019   0.04134  -0.0335   0.9690   0.0695
  -6.500  -0.5305   0.04762   0.03827  -0.0334   0.9610   0.0712
  -6.250  -0.5087   0.04530   0.03537  -0.0333   0.9536   0.0728
  -6.000  -0.4835   0.04335   0.03311  -0.0336   0.9462   0.0741
  -5.750  -0.4550   0.04170   0.03126  -0.0342   0.9395   0.0753
  -5.500  -0.4282   0.04029   0.02966  -0.0344   0.9314   0.0769
  -5.250  -0.3946   0.03903   0.02818  -0.0357   0.9251   0.0799
  -5.000  -0.3691   0.03793   0.02681  -0.0353   0.9158   0.0825
  -4.750  -0.3304   0.03672   0.02544  -0.0372   0.9101   0.0853
  -4.500  -0.3061   0.03581   0.02452  -0.0366   0.8998   0.0876
  -4.250  -0.2659   0.03488   0.02350  -0.0386   0.8938   0.0918
  -4.000  -0.2416   0.03419   0.02270  -0.0378   0.8826   0.0964
  -3.750  -0.2091   0.03341   0.02197  -0.0386   0.8740   0.1025
  -3.500  -0.1771   0.03268   0.02115  -0.0392   0.8646   0.1096
  -3.250  -0.1497   0.03201   0.02048  -0.0390   0.8539   0.1210
  -3.000  -0.1121   0.03098   0.01964  -0.0407   0.8461   0.1486
  -2.750  -0.0918   0.02997   0.01909  -0.0395   0.8340   0.2095
  -2.500  -0.0688   0.02879   0.01863  -0.0387   0.8240   0.3555
  -2.250  -0.0469   0.02754   0.01843  -0.0367   0.8142   0.5459
  -2.000   0.0787   0.02788   0.01972  -0.0489   0.8129   0.9041
  -1.750   0.1621   0.02808   0.01954  -0.0579   0.8026   0.9464
  -1.500   0.2468   0.02757   0.01867  -0.0676   0.7957   0.9719
  -1.250   0.3120   0.02710   0.01793  -0.0745   0.7824   0.9899
  -1.000   0.3667   0.02654   0.01715  -0.0795   0.7687   1.0000
  -0.750   0.3925   0.02610   0.01652  -0.0791   0.7534   1.0000
  -0.500   0.4190   0.02568   0.01592  -0.0786   0.7377   1.0000
  -0.250   0.4452   0.02531   0.01537  -0.0781   0.7210   1.0000
   0.000   0.4704   0.02502   0.01489  -0.0773   0.7036   1.0000
   0.250   0.4945   0.02479   0.01448  -0.0763   0.6853   1.0000
   0.500   0.5175   0.02463   0.01414  -0.0752   0.6662   1.0000
   0.750   0.5399   0.02453   0.01386  -0.0739   0.6470   1.0000
   1.000   0.5613   0.02450   0.01364  -0.0725   0.6278   1.0000
   1.250   0.5817   0.02453   0.01349  -0.0710   0.6087   1.0000
   1.500   0.6009   0.02462   0.01341  -0.0692   0.5902   1.0000
   1.750   0.6192   0.02477   0.01338  -0.0674   0.5720   1.0000
   2.000   0.6365   0.02495   0.01340  -0.0654   0.5543   1.0000
   2.250   0.6536   0.02518   0.01347  -0.0633   0.5375   1.0000
   2.500   0.6704   0.02544   0.01358  -0.0613   0.5213   1.0000
   2.750   0.6879   0.02573   0.01371  -0.0594   0.5062   1.0000
   3.000   0.7063   0.02602   0.01383  -0.0576   0.4922   1.0000
   3.250   0.7237   0.02637   0.01405  -0.0558   0.4787   1.0000
   3.500   0.7396   0.02679   0.01438  -0.0537   0.4659   1.0000
   3.750   0.7582   0.02719   0.01465  -0.0522   0.4542   1.0000
   4.000   0.7784   0.02758   0.01491  -0.0508   0.4433   1.0000
   4.250   0.7939   0.02809   0.01538  -0.0488   0.4324   1.0000
   4.500   0.8170   0.02851   0.01564  -0.0480   0.4233   1.0000
   4.750   0.8320   0.02909   0.01623  -0.0460   0.4137   1.0000
   5.000   0.8569   0.02955   0.01654  -0.0456   0.4061   1.0000
   5.250   0.8699   0.03022   0.01726  -0.0433   0.3976   1.0000
   5.500   0.8934   0.03072   0.01765  -0.0427   0.3905   1.0000
   5.750   0.9078   0.03142   0.01839  -0.0407   0.3832   1.0000
   6.000   0.9256   0.03205   0.01901  -0.0392   0.3763   1.0000
   6.250   0.9508   0.03263   0.01948  -0.0389   0.3707   1.0000
   6.500   0.9604   0.03351   0.02049  -0.0363   0.3646   1.0000
   6.750   0.9782   0.03423   0.02122  -0.0349   0.3590   1.0000
   7.000   1.0065   0.03480   0.02167  -0.0351   0.3542   1.0000
   7.250   1.0095   0.03587   0.02292  -0.0316   0.3486   1.0000
   7.500   1.0221   0.03677   0.02390  -0.0296   0.3435   1.0000
   7.750   1.0445   0.03747   0.02457  -0.0290   0.3391   1.0000
   8.000   1.0601   0.03842   0.02556  -0.0275   0.3350   1.0000
   8.250   1.0582   0.03972   0.02703  -0.0235   0.3306   1.0000
   8.500   1.0660   0.04081   0.02822  -0.0210   0.3263   1.0000
   8.750   1.0867   0.04160   0.02900  -0.0203   0.3223   1.0000
   9.000   1.1024   0.04260   0.03003  -0.0189   0.3186   1.0000
   9.250   1.0863   0.04457   0.03222  -0.0137   0.3148   1.0000
   9.500   1.0798   0.04643   0.03423  -0.0101   0.3109   1.0000
   9.750   1.0881   0.04776   0.03564  -0.0083   0.3072   1.0000
  10.000   1.1188   0.04821   0.03607  -0.0087   0.3037   1.0000
  10.250   1.0927   0.05118   0.03924  -0.0039   0.3003   1.0000
  10.500   1.0301   0.05700   0.04534   0.0019   0.2959   1.0000
  10.750   0.9909   0.06246   0.05095   0.0044   0.2910   1.0000
  11.000   1.0169   0.06267   0.05117   0.0049   0.2880   1.0000
  11.500   0.8511   0.08853   0.07731   0.0020   0.2706   1.0000
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