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GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 360 AIRFOIL (goe360-il)
Reynolds number: 100,000
Max Cl/Cd: 51.39 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe360-il-100000.txt
Download as CSV file: xf-goe360-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 360 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2893   0.09916   0.09506  -0.0232   1.0000   0.0516
  -7.250  -0.3081   0.09883   0.09484  -0.0195   1.0000   0.0518
  -7.000  -0.3239   0.09819   0.09431  -0.0169   1.0000   0.0522
  -6.750  -0.3015   0.09424   0.09034  -0.0231   0.9939   0.0544
  -6.500  -0.2557   0.09016   0.08615  -0.0403   0.9815   0.0587
  -6.250  -0.2124   0.08503   0.08089  -0.0550   0.9711   0.0600
  -6.000  -0.1945   0.07965   0.07556  -0.0536   0.9638   0.0616
  -5.750  -0.1592   0.07501   0.07087  -0.0595   0.9572   0.0647
  -5.500  -0.1209   0.07100   0.06674  -0.0681   0.9463   0.0691
  -5.250  -0.0699   0.06634   0.06186  -0.0810   0.9376   0.0734
  -5.000  -0.0422   0.06218   0.05771  -0.0831   0.9296   0.0772
  -4.750   0.0191   0.06156   0.05644  -0.0961   0.9172   0.0859
  -4.500   0.0399   0.05482   0.04994  -0.0968   0.9115   0.0881
  -4.250   0.0634   0.05195   0.04705  -0.0979   0.8995   0.0927
  -4.000   0.1010   0.04960   0.04435  -0.1028   0.8877   0.1018
  -3.750   0.1264   0.04646   0.04124  -0.1035   0.8798   0.1091
  -3.500   0.1521   0.04424   0.03880  -0.1049   0.8666   0.1188
  -3.250   0.1794   0.04263   0.03692  -0.1062   0.8540   0.1318
  -3.000   0.2047   0.04098   0.03507  -0.1066   0.8424   0.1465
  -2.750   0.2294   0.03850   0.03250  -0.1068   0.8338   0.1625
  -2.500   0.2490   0.03643   0.03041  -0.1062   0.8210   0.1798
  -1.500   0.3018   0.01272   0.00722  -0.0925   0.7538   0.3772
  -1.250   0.3199   0.01106   0.00559  -0.0906   0.7439   0.4310
  -1.000   0.3417   0.00984   0.00435  -0.0894   0.7328   0.4698
  -0.750   0.3768   0.00890   0.00307  -0.0911   0.7232   0.4744
  -0.500   0.4307   0.00879   0.00212  -0.0962   0.7129   0.3626
  -0.250   0.5069   0.02427   0.01594  -0.1043   0.7217   0.1899
   0.000   0.5393   0.02330   0.01456  -0.1034   0.7115   0.1564
   0.250   0.5686   0.02259   0.01354  -0.1024   0.6987   0.1352
   0.500   0.5970   0.02202   0.01273  -0.1016   0.6862   0.1227
   0.750   0.6255   0.02175   0.01216  -0.1006   0.6741   0.1140
   1.000   0.6531   0.02106   0.01135  -0.1000   0.6628   0.1104
   1.250   0.6802   0.02063   0.01080  -0.0992   0.6508   0.1078
   1.500   0.7062   0.02037   0.01050  -0.0985   0.6378   0.1088
   1.750   0.7317   0.02020   0.01028  -0.0977   0.6254   0.1123
   2.000   0.7578   0.02008   0.01005  -0.0969   0.6142   0.1139
   2.250   0.7849   0.01997   0.00979  -0.0964   0.6035   0.1166
   2.500   0.8106   0.02004   0.00981  -0.0959   0.5911   0.1228
   2.750   0.8370   0.02014   0.00986  -0.0955   0.5799   0.1368
   3.000   0.8650   0.01853   0.00983  -0.0951   0.5712   1.0000
   3.250   0.8900   0.01895   0.01005  -0.0945   0.5597   1.0000
   3.500   0.9157   0.01934   0.01026  -0.0940   0.5500   1.0000
   3.750   0.9425   0.01964   0.01037  -0.0937   0.5414   1.0000
   4.000   0.9669   0.02010   0.01080  -0.0932   0.5313   1.0000
   4.250   0.9942   0.02041   0.01095  -0.0930   0.5240   1.0000
   4.500   1.0182   0.02093   0.01151  -0.0926   0.5147   1.0000
   4.750   1.0448   0.02131   0.01180  -0.0924   0.5079   1.0000
   5.000   1.0690   0.02183   0.01237  -0.0920   0.4993   1.0000
   5.250   1.0957   0.02223   0.01268  -0.0918   0.4930   1.0000
   5.500   1.1190   0.02286   0.01344  -0.0914   0.4851   1.0000
   5.750   1.1466   0.02326   0.01375  -0.0914   0.4798   1.0000
   6.000   1.1684   0.02406   0.01471  -0.0908   0.4724   1.0000
   6.250   1.1947   0.02452   0.01516  -0.0907   0.4665   1.0000
   6.500   1.2183   0.02526   0.01600  -0.0903   0.4606   1.0000
   6.750   1.2413   0.02603   0.01690  -0.0899   0.4545   1.0000
   7.000   1.2684   0.02657   0.01742  -0.0899   0.4500   1.0000
   7.250   1.2884   0.02763   0.01869  -0.0892   0.4441   1.0000
   7.500   1.3112   0.02842   0.01963  -0.0888   0.4385   1.0000
   7.750   1.3390   0.02897   0.02018  -0.0889   0.4344   1.0000
   8.000   1.3551   0.03040   0.02191  -0.0879   0.4290   1.0000
   8.250   1.3758   0.03144   0.02313  -0.0873   0.4239   1.0000
   8.500   1.4060   0.03153   0.02318  -0.0874   0.4178   1.0000
   8.750   1.4228   0.03201   0.02387  -0.0859   0.4074   1.0000
   9.000   1.4452   0.03181   0.02372  -0.0848   0.3955   1.0000
   9.250   1.4716   0.03148   0.02338  -0.0842   0.3849   1.0000
   9.500   1.4986   0.03094   0.02277  -0.0836   0.3730   1.0000
   9.750   1.5134   0.03100   0.02304  -0.0816   0.3604   1.0000
  10.000   1.5303   0.03064   0.02276  -0.0797   0.3455   1.0000
  10.250   1.5448   0.03016   0.02234  -0.0774   0.3287   1.0000
  10.500   1.5474   0.03011   0.02247  -0.0737   0.3086   1.0000
  10.750   1.5439   0.03037   0.02286  -0.0694   0.2850   1.0000
  11.000   1.5338   0.03133   0.02394  -0.0646   0.2579   1.0000
  11.250   1.5191   0.03332   0.02587  -0.0606   0.2143   1.0000
  11.500   1.4954   0.03686   0.02902  -0.0573   0.1529   1.0000
  11.750   1.4679   0.04158   0.03340  -0.0550   0.1140   1.0000
  12.000   1.4433   0.04669   0.03838  -0.0539   0.0951   1.0000
  12.250   1.4212   0.05205   0.04375  -0.0536   0.0848   1.0000
  12.500   1.4009   0.05760   0.04938  -0.0538   0.0782   1.0000
  12.750   1.3806   0.06341   0.05531  -0.0545   0.0741   1.0000
  13.000   1.3596   0.06954   0.06154  -0.0555   0.0717   1.0000
  13.250   1.3418   0.07548   0.06761  -0.0566   0.0690   1.0000
  13.500   1.3258   0.08130   0.07357  -0.0577   0.0665   1.0000
  13.750   1.3109   0.08703   0.07941  -0.0589   0.0642   1.0000
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