Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 650 AIRFOIL (goe650-il)
Reynolds number: 50,000
Max Cl/Cd: 31.83 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe650-il-50000.txt
Download as CSV file: xf-goe650-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 650 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3427   0.11852   0.11138  -0.0239   1.0000   0.2760
  -8.500  -0.3075   0.11211   0.10491  -0.0223   1.0000   0.2843
  -8.250  -0.3269   0.11203   0.10495  -0.0201   1.0000   0.2919
  -8.000  -0.3474   0.11117   0.10422  -0.0180   1.0000   0.2950
  -7.750  -0.3247   0.10683   0.09985  -0.0162   1.0000   0.3032
  -7.500  -0.3528   0.10728   0.10044  -0.0134   1.0000   0.3101
  -7.250  -0.3563   0.10456   0.09779  -0.0115   1.0000   0.3143
  -7.000  -0.3530   0.10242   0.09568  -0.0091   1.0000   0.3254
  -6.750  -0.3958   0.10364   0.09707  -0.0052   1.0000   0.3290
  -6.500  -0.3663   0.09863   0.09202  -0.0042   1.0000   0.3409
  -6.250  -0.4050   0.09932   0.09286   0.0000   1.0000   0.3464
  -6.000  -0.3882   0.09521   0.08874   0.0013   1.0000   0.3558
  -5.750  -0.4175   0.09500   0.08865   0.0054   1.0000   0.3634
  -5.500  -0.4205   0.09222   0.08592   0.0077   1.0000   0.3712
  -5.250  -0.4810   0.07843   0.07199  -0.0144   1.0000   0.2574
  -5.000  -0.4763   0.07396   0.06748  -0.0154   1.0000   0.2548
  -4.750  -0.4690   0.06798   0.06135  -0.0208   1.0000   0.2544
  -4.500  -0.4481   0.05781   0.05059  -0.0347   1.0000   0.2587
  -4.250  -0.4432   0.06047   0.05356  -0.0257   1.0000   0.2707
  -4.000  -0.4245   0.05632   0.04917  -0.0298   1.0000   0.2798
  -3.750  -0.4070   0.05410   0.04681  -0.0308   1.0000   0.2889
  -3.500  -0.3817   0.04991   0.04224  -0.0358   1.0000   0.2961
  -3.250  -0.3660   0.04898   0.04128  -0.0346   1.0000   0.3032
  -3.000  -0.3370   0.04539   0.03718  -0.0396   1.0000   0.3102
  -2.750  -0.3202   0.04449   0.03627  -0.0388   1.0000   0.3169
  -2.500  -0.2986   0.04301   0.03457  -0.0398   1.0000   0.3238
  -2.250  -0.2753   0.04141   0.03267  -0.0414   1.0000   0.3320
  -2.000  -0.2576   0.04092   0.03215  -0.0408   1.0000   0.3397
  -1.750  -0.2336   0.03966   0.03052  -0.0424   1.0000   0.3488
  -1.500  -0.2172   0.03946   0.03038  -0.0414   1.0000   0.3566
  -1.250  -0.1960   0.03887   0.02955  -0.0419   1.0000   0.3681
  -1.000  -0.1787   0.03875   0.02943  -0.0413   1.0000   0.3774
  -0.750  -0.1592   0.03849   0.02905  -0.0413   1.0000   0.3889
  -0.500  -0.1392   0.03843   0.02883  -0.0415   1.0000   0.4034
  -0.250  -0.1225   0.03854   0.02900  -0.0407   1.0000   0.4160
   0.000  -0.1049   0.03865   0.02909  -0.0403   1.0000   0.4302
   0.250  -0.0371   0.04040   0.03076  -0.0483   0.9742   0.4632
   0.500   0.0103   0.04136   0.03167  -0.0525   0.9570   0.4950
   0.750   0.0549   0.04215   0.03244  -0.0561   0.9399   0.5296
   1.000   0.0935   0.04264   0.03296  -0.0585   0.9228   0.5641
   1.250   0.1322   0.04308   0.03343  -0.0608   0.9057   0.6016
   1.500   0.1710   0.04343   0.03388  -0.0629   0.8892   0.6419
   1.750   0.2116   0.04372   0.03426  -0.0652   0.8731   0.6892
   2.000   0.2567   0.04372   0.03453  -0.0681   0.8576   0.7482
   2.250   0.3091   0.04308   0.03457  -0.0728   0.8399   1.0000
   2.500   0.3584   0.04391   0.03506  -0.0782   0.8220   1.0000
   2.750   0.4010   0.04462   0.03552  -0.0816   0.8043   1.0000
   3.000   0.4397   0.04523   0.03593  -0.0837   0.7865   1.0000
   3.250   0.4762   0.04575   0.03631  -0.0851   0.7687   1.0000
   3.500   0.5109   0.04619   0.03665  -0.0860   0.7506   1.0000
   3.750   0.5450   0.04655   0.03694  -0.0867   0.7322   1.0000
   4.000   0.5788   0.04680   0.03715  -0.0870   0.7138   1.0000
   4.250   0.6129   0.04695   0.03727  -0.0872   0.6955   1.0000
   4.500   0.6479   0.04692   0.03723  -0.0872   0.6774   1.0000
   4.750   0.6830   0.04676   0.03706  -0.0871   0.6598   1.0000
   5.000   0.7200   0.04632   0.03662  -0.0869   0.6427   1.0000
   5.250   0.7926   0.04329   0.03365  -0.0888   0.6325   1.0000
   5.500   0.8354   0.04203   0.03241  -0.0886   0.6162   1.0000
   5.750   0.8829   0.04052   0.03095  -0.0889   0.5998   1.0000
   6.000   0.9450   0.03827   0.02875  -0.0907   0.5828   1.0000
   6.250   1.0117   0.03592   0.02636  -0.0932   0.5645   1.0000
   6.500   1.0398   0.03590   0.02634  -0.0920   0.5437   1.0000
   6.750   1.0721   0.03584   0.02624  -0.0914   0.5229   1.0000
   7.000   1.1068   0.03583   0.02616  -0.0912   0.5023   1.0000
   7.250   1.1389   0.03612   0.02639  -0.0908   0.4826   1.0000
   7.500   1.1672   0.03667   0.02688  -0.0901   0.4638   1.0000
   7.750   1.1891   0.03760   0.02778  -0.0888   0.4468   1.0000
   8.000   1.2080   0.03867   0.02888  -0.0872   0.4308   1.0000
   8.250   1.2257   0.03990   0.03013  -0.0855   0.4161   1.0000
   8.500   1.2467   0.04107   0.03130  -0.0843   0.4024   1.0000
   8.750   1.2745   0.04204   0.03221  -0.0839   0.3890   1.0000
   9.000   1.2846   0.04372   0.03402  -0.0815   0.3776   1.0000
   9.250   1.2888   0.04588   0.03634  -0.0787   0.3679   1.0000
   9.500   1.3256   0.04681   0.03716  -0.0794   0.3565   1.0000
   9.750   1.2997   0.05018   0.04088  -0.0735   0.3500   1.0000
  10.000   1.3439   0.05103   0.04164  -0.0751   0.3397   1.0000
  10.250   1.3003   0.05542   0.04639  -0.0680   0.3362   1.0000
  10.500   1.2350   0.06134   0.05251  -0.0604   0.3343   1.0000
  10.750   0.9630   0.09699   0.08809  -0.0644   0.3391   1.0000
  11.000   0.9166   0.10880   0.09988  -0.0685   0.3390   1.0000
<< Back to GOE 650 AIRFOIL (goe650-il)

Polar data table (+)

Polar graphs


<< Back to GOE 650 AIRFOIL (goe650-il)