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GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 565 AIRFOIL (goe565-il)
Reynolds number: 100,000
Max Cl/Cd: 56.93 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe565-il-100000.txt
Download as CSV file: xf-goe565-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 565 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4256   0.10644   0.10117  -0.0264   1.0000   0.0990
  -9.250  -0.4430   0.10483   0.09969  -0.0309   1.0000   0.1013
  -9.000  -0.4633   0.10309   0.09811  -0.0346   1.0000   0.1018
  -8.750  -0.4245   0.09651   0.09140  -0.0285   1.0000   0.1059
  -8.500  -0.3496   0.08417   0.07947  -0.0312   1.0000   0.1192
  -8.250  -0.3421   0.08118   0.07650  -0.0298   1.0000   0.1250
  -8.000  -0.3586   0.07854   0.07395  -0.0308   1.0000   0.1293
  -7.750  -0.3868   0.07657   0.07214  -0.0315   1.0000   0.1304
  -7.500  -0.3702   0.07177   0.06733  -0.0289   1.0000   0.1346
  -7.250  -0.3705   0.06917   0.06476  -0.0268   1.0000   0.1390
  -7.000  -0.3903   0.06703   0.06275  -0.0254   1.0000   0.1423
  -6.750  -0.4310   0.06379   0.05955  -0.0322   1.0000   0.1456
  -6.500  -0.4171   0.06024   0.05609  -0.0260   1.0000   0.1487
  -6.250  -0.4608   0.06688   0.06234  -0.0307   1.0000   0.1498
  -6.000  -0.4631   0.06297   0.05827  -0.0352   1.0000   0.1615
  -5.750  -0.4579   0.06064   0.05574  -0.0366   1.0000   0.1751
  -5.500  -0.4486   0.05778   0.05313  -0.0308   1.0000   0.1785
  -5.250  -0.4412   0.05539   0.05072  -0.0297   1.0000   0.1934
  -5.000  -0.4111   0.03967   0.03318  -0.0429   1.0000   0.1169
  -4.750  -0.3893   0.03429   0.02706  -0.0427   1.0000   0.1014
  -4.500  -0.3696   0.03117   0.02346  -0.0422   1.0000   0.1026
  -4.250  -0.3477   0.02895   0.02079  -0.0414   1.0000   0.1023
  -4.000  -0.3274   0.02673   0.01860  -0.0410   1.0000   0.1066
  -3.750  -0.3046   0.02523   0.01679  -0.0402   1.0000   0.1094
  -3.500  -0.2809   0.02382   0.01501  -0.0395   1.0000   0.1108
  -3.250  -0.2579   0.02296   0.01380  -0.0386   1.0000   0.1150
  -3.000  -0.2349   0.02179   0.01244  -0.0378   1.0000   0.1182
  -2.750  -0.2124   0.02084   0.01144  -0.0370   1.0000   0.1213
  -2.500  -0.1901   0.02016   0.01069  -0.0362   1.0000   0.1253
  -2.250  -0.1681   0.01969   0.01007  -0.0353   1.0000   0.1317
  -2.000  -0.1466   0.01900   0.00953  -0.0345   1.0000   0.1391
  -1.750  -0.1251   0.01858   0.00909  -0.0335   1.0000   0.1465
  -1.500  -0.1041   0.01811   0.00876  -0.0326   1.0000   0.1585
  -1.250  -0.0829   0.01768   0.00853  -0.0319   1.0000   0.1832
  -1.000  -0.0591   0.01633   0.00863  -0.0316   1.0000   0.4550
  -0.750  -0.0119   0.01516   0.00882  -0.0347   0.9961   1.0000
  -0.500   0.0328   0.01570   0.00906  -0.0386   0.9875   1.0000
  -0.250   0.0769   0.01622   0.00934  -0.0423   0.9786   1.0000
   0.000   0.1257   0.01675   0.00970  -0.0469   0.9699   1.0000
   0.250   0.1695   0.01706   0.00986  -0.0503   0.9581   1.0000
   0.500   0.2131   0.01732   0.01002  -0.0536   0.9459   1.0000
   0.750   0.2562   0.01753   0.01016  -0.0567   0.9344   1.0000
   1.000   0.3038   0.01770   0.01028  -0.0605   0.9248   1.0000
   1.250   0.3459   0.01779   0.01035  -0.0632   0.9137   1.0000
   1.500   0.3863   0.01778   0.01035  -0.0654   0.9010   1.0000
   1.750   0.4314   0.01760   0.01019  -0.0682   0.8881   1.0000
   2.000   0.4799   0.01725   0.00989  -0.0713   0.8756   1.0000
   2.250   0.5262   0.01675   0.00945  -0.0737   0.8622   1.0000
   2.500   0.5671   0.01626   0.00902  -0.0750   0.8475   1.0000
   2.750   0.6043   0.01576   0.00860  -0.0754   0.8308   1.0000
   3.000   0.6394   0.01531   0.00821  -0.0755   0.8134   1.0000
   3.250   0.6732   0.01494   0.00790  -0.0754   0.7958   1.0000
   3.500   0.7015   0.01472   0.00775  -0.0743   0.7731   1.0000
   3.750   0.7324   0.01445   0.00750  -0.0736   0.7496   1.0000
   4.000   0.7595   0.01437   0.00742  -0.0724   0.7214   1.0000
   4.250   0.7849   0.01440   0.00746  -0.0710   0.6898   1.0000
   4.500   0.8080   0.01451   0.00755  -0.0692   0.6518   1.0000
   4.750   0.8300   0.01464   0.00756  -0.0672   0.6060   1.0000
   5.000   0.8500   0.01493   0.00762  -0.0648   0.5518   1.0000
   5.250   0.8683   0.01546   0.00788  -0.0625   0.4949   1.0000
   5.500   0.8855   0.01610   0.00824  -0.0602   0.4382   1.0000
   5.750   0.9033   0.01678   0.00871  -0.0581   0.3877   1.0000
   6.000   0.9210   0.01752   0.00924  -0.0563   0.3428   1.0000
   6.250   0.9389   0.01827   0.00986  -0.0545   0.3028   1.0000
   6.500   0.9562   0.01901   0.01047  -0.0527   0.2611   1.0000
   6.750   0.9705   0.02001   0.01122  -0.0506   0.2062   1.0000
   7.000   0.9780   0.02208   0.01274  -0.0474   0.1360   1.0000
   7.250   0.9931   0.02346   0.01389  -0.0453   0.1080   1.0000
   7.500   1.0098   0.02488   0.01518  -0.0435   0.0954   1.0000
   7.750   1.0287   0.02626   0.01660  -0.0419   0.0857   1.0000
   8.000   1.0499   0.02811   0.01843  -0.0408   0.0792   1.0000
   8.250   1.0727   0.02983   0.02022  -0.0399   0.0735   1.0000
   8.500   1.0969   0.03225   0.02262  -0.0394   0.0683   1.0000
   8.750   1.1200   0.03437   0.02509  -0.0384   0.0652   1.0000
   9.000   1.1416   0.03676   0.02773  -0.0373   0.0625   1.0000
   9.250   1.1612   0.03924   0.03027  -0.0365   0.0593   1.0000
   9.500   1.1769   0.04308   0.03440  -0.0352   0.0574   1.0000
   9.750   1.1864   0.04619   0.03801  -0.0328   0.0569   1.0000
  10.000   1.1919   0.04979   0.04208  -0.0303   0.0567   1.0000
  10.250   1.1937   0.05375   0.04646  -0.0277   0.0569   1.0000
  10.500   1.1906   0.05770   0.05081  -0.0249   0.0569   1.0000
  10.750   1.1833   0.06174   0.05520  -0.0220   0.0571   1.0000
  11.000   1.1713   0.06568   0.05944  -0.0192   0.0571   1.0000
  11.250   1.1549   0.06944   0.06343  -0.0161   0.0573   1.0000
  11.500   1.1395   0.07383   0.06799  -0.0140   0.0576   1.0000
  11.750   1.1248   0.07830   0.07265  -0.0127   0.0580   1.0000
  12.000   1.0146   0.08907   0.08413  -0.0181   0.0644   1.0000
  12.250   0.9768   0.09973   0.09488  -0.0253   0.0661   1.0000
  12.500   0.9573   0.10897   0.10412  -0.0306   0.0680   1.0000
  12.750   0.9168   0.12901   0.12409  -0.0421   0.0815   1.0000
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