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GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 564 AIRFOIL (goe564-il)
Reynolds number: 100,000
Max Cl/Cd: 55.98 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe564-il-100000.txt
Download as CSV file: xf-goe564-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 564 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4326   0.09893   0.09381  -0.0281   1.0000   0.1075
  -8.500  -0.4534   0.09738   0.09241  -0.0308   1.0000   0.1090
  -8.250  -0.4765   0.09549   0.09065  -0.0333   1.0000   0.1095
  -8.000  -0.4632   0.09027   0.08546  -0.0298   1.0000   0.1115
  -7.750  -0.4476   0.08691   0.08208  -0.0270   1.0000   0.1147
  -7.500  -0.4532   0.08442   0.07966  -0.0259   1.0000   0.1171
  -7.250  -0.4615   0.08155   0.07686  -0.0269   1.0000   0.1207
  -7.000  -0.4935   0.07925   0.07442  -0.0361   1.0000   0.1245
  -6.750  -0.4831   0.07423   0.06956  -0.0322   1.0000   0.1260
  -6.500  -0.4749   0.07147   0.06686  -0.0284   1.0000   0.1285
  -6.250  -0.4720   0.06889   0.06426  -0.0272   1.0000   0.1342
  -6.000  -0.4771   0.06469   0.05987  -0.0313   1.0000   0.1409
  -5.750  -0.4684   0.06225   0.05755  -0.0274   1.0000   0.1449
  -5.500  -0.4648   0.05872   0.05371  -0.0306   1.0000   0.1557
  -5.250  -0.4554   0.05565   0.05074  -0.0279   1.0000   0.1585
  -5.000  -0.4454   0.05265   0.04746  -0.0292   1.0000   0.1710
  -4.750  -0.4342   0.04986   0.04477  -0.0269   1.0000   0.1751
  -4.500  -0.4222   0.04734   0.04214  -0.0263   1.0000   0.1897
  -4.250  -0.3806   0.03249   0.02498  -0.0320   1.0000   0.0945
  -4.000  -0.3598   0.02982   0.02188  -0.0311   1.0000   0.0944
  -3.750  -0.3390   0.02774   0.01954  -0.0304   1.0000   0.0980
  -3.500  -0.3171   0.02622   0.01781  -0.0295   1.0000   0.1005
  -3.250  -0.2941   0.02469   0.01595  -0.0286   1.0000   0.1026
  -3.000  -0.2711   0.02344   0.01438  -0.0276   1.0000   0.1064
  -2.750  -0.2488   0.02241   0.01314  -0.0267   1.0000   0.1131
  -2.500  -0.2267   0.02161   0.01223  -0.0257   1.0000   0.1198
  -2.250  -0.2040   0.02065   0.01116  -0.0248   1.0000   0.1285
  -2.000  -0.1821   0.01990   0.01040  -0.0238   1.0000   0.1433
  -1.750  -0.1611   0.01936   0.00990  -0.0229   1.0000   0.1667
  -1.500  -0.1405   0.01881   0.00946  -0.0219   1.0000   0.1899
  -1.250  -0.1203   0.01854   0.00924  -0.0210   1.0000   0.2137
  -1.000  -0.1011   0.01832   0.00921  -0.0200   1.0000   0.2418
  -0.750  -0.0812   0.01813   0.00920  -0.0192   1.0000   0.2718
  -0.500  -0.0405   0.01786   0.00939  -0.0223   0.9935   0.3444
  -0.250   0.0202   0.01626   0.00952  -0.0283   0.9903   1.0000
   0.000   0.0664   0.01687   0.00987  -0.0325   0.9812   1.0000
   0.250   0.1125   0.01741   0.01022  -0.0366   0.9717   1.0000
   0.500   0.1534   0.01778   0.01047  -0.0397   0.9606   1.0000
   0.750   0.1943   0.01814   0.01073  -0.0426   0.9498   1.0000
   1.000   0.2392   0.01841   0.01093  -0.0462   0.9386   1.0000
   1.250   0.2888   0.01846   0.01094  -0.0503   0.9254   1.0000
   1.500   0.3406   0.01823   0.01069  -0.0543   0.9099   1.0000
   1.750   0.3926   0.01781   0.01028  -0.0580   0.8948   1.0000
   2.000   0.4511   0.01729   0.00981  -0.0631   0.8856   1.0000
   2.250   0.4907   0.01703   0.00960  -0.0647   0.8730   1.0000
   2.500   0.5307   0.01671   0.00937  -0.0664   0.8604   1.0000
   2.750   0.5709   0.01631   0.00904  -0.0678   0.8472   1.0000
   3.000   0.6106   0.01585   0.00867  -0.0690   0.8326   1.0000
   3.250   0.6496   0.01532   0.00825  -0.0698   0.8153   1.0000
   3.500   0.6832   0.01491   0.00790  -0.0696   0.7940   1.0000
   3.750   0.7145   0.01450   0.00754  -0.0689   0.7672   1.0000
   4.000   0.7382   0.01428   0.00736  -0.0669   0.7315   1.0000
   4.250   0.7647   0.01409   0.00712  -0.0653   0.6882   1.0000
   4.500   0.7910   0.01413   0.00696  -0.0637   0.6345   1.0000
   4.750   0.8106   0.01454   0.00708  -0.0612   0.5632   1.0000
   5.000   0.8250   0.01518   0.00733  -0.0580   0.4777   1.0000
   5.250   0.8404   0.01608   0.00773  -0.0553   0.4134   1.0000
   5.500   0.8586   0.01697   0.00832  -0.0534   0.3718   1.0000
   5.750   0.8785   0.01782   0.00897  -0.0519   0.3414   1.0000
   6.000   0.8987   0.01859   0.00966  -0.0505   0.3145   1.0000
   6.250   0.9183   0.01937   0.01035  -0.0490   0.2885   1.0000
   6.500   0.9374   0.02018   0.01106  -0.0475   0.2637   1.0000
   6.750   0.9558   0.02099   0.01178  -0.0460   0.2395   1.0000
   7.000   0.9731   0.02172   0.01253  -0.0442   0.2142   1.0000
   7.250   0.9897   0.02249   0.01334  -0.0423   0.1894   1.0000
   7.500   1.0034   0.02320   0.01406  -0.0400   0.1590   1.0000
   7.750   1.0142   0.02414   0.01485  -0.0371   0.1204   1.0000
   8.000   1.0271   0.02577   0.01621  -0.0347   0.0974   1.0000
   8.250   1.0442   0.02765   0.01801  -0.0330   0.0838   1.0000
   8.500   1.0642   0.02943   0.01984  -0.0318   0.0749   1.0000
   8.750   1.0877   0.03178   0.02233  -0.0310   0.0691   1.0000
   9.000   1.1069   0.03344   0.02413  -0.0297   0.0636   1.0000
   9.250   1.1295   0.03629   0.02701  -0.0292   0.0597   1.0000
   9.500   1.1466   0.03878   0.02994  -0.0274   0.0578   1.0000
   9.750   1.1599   0.04152   0.03311  -0.0253   0.0561   1.0000
  10.000   1.1704   0.04407   0.03602  -0.0231   0.0542   1.0000
  10.250   1.1823   0.04626   0.03833  -0.0213   0.0518   1.0000
  10.500   1.1899   0.04951   0.04179  -0.0194   0.0506   1.0000
  10.750   1.1900   0.05323   0.04588  -0.0166   0.0504   1.0000
  11.000   1.1840   0.05680   0.04984  -0.0133   0.0505   1.0000
  11.250   1.1688   0.06014   0.05359  -0.0091   0.0509   1.0000
  11.500   1.1412   0.06363   0.05747  -0.0044   0.0516   1.0000
  11.750   1.1004   0.06829   0.06255  -0.0011   0.0528   1.0000
  12.000   1.0645   0.07382   0.06836  -0.0006   0.0535   1.0000
  12.250   1.0262   0.08083   0.07560  -0.0029   0.0546   1.0000
  12.500   0.9876   0.08977   0.08469  -0.0082   0.0559   1.0000
  12.750   0.9532   0.10052   0.09552  -0.0153   0.0578   1.0000
  13.000   0.9293   0.11094   0.10594  -0.0215   0.0591   1.0000
  13.250   0.9225   0.11770   0.11268  -0.0240   0.0601   1.0000
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