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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 50,000
Max Cl/Cd: 38.79 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610b-il-50000-n5.txt
Download as CSV file: xf-goe610b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2912   0.10315   0.09673  -0.0336   1.0000   0.0786
  -7.750  -0.3011   0.10218   0.09590  -0.0321   1.0000   0.0816
  -7.500  -0.3153   0.10154   0.09542  -0.0299   1.0000   0.0825
  -7.250  -0.3326   0.10148   0.09551  -0.0287   1.0000   0.0836
  -7.000  -0.3462   0.10108   0.09523  -0.0285   1.0000   0.0841
  -6.750  -0.3562   0.10051   0.09473  -0.0296   1.0000   0.0845
  -6.500  -0.3474   0.09468   0.08897  -0.0236   0.9992   0.0878
  -6.250  -0.3242   0.09064   0.08488  -0.0288   0.9905   0.0936
  -6.000  -0.2901   0.08768   0.08178  -0.0450   0.9768   0.0985
  -5.750  -0.2784   0.08241   0.07657  -0.0405   0.9717   0.1036
  -5.500  -0.2467   0.07915   0.07315  -0.0520   0.9597   0.1130
  -5.250  -0.2293   0.07469   0.06870  -0.0510   0.9530   0.1200
  -5.000  -0.1963   0.07128   0.06505  -0.0607   0.9414   0.1273
  -4.750  -0.1733   0.06685   0.06062  -0.0616   0.9357   0.1333
  -4.500  -0.1493   0.06353   0.05718  -0.0655   0.9250   0.1451
  -4.250  -0.1211   0.06014   0.05363  -0.0697   0.9161   0.1588
  -4.000  -0.0630   0.05390   0.04654  -0.0803   0.9082   0.0980
  -3.500  -0.0012   0.04703   0.03915  -0.0855   0.8929   0.0967
  -3.250   0.0267   0.04411   0.03599  -0.0870   0.8842   0.0940
  -3.000   0.0637   0.04128   0.03273  -0.0899   0.8780   0.0943
  -2.750   0.0930   0.03933   0.03030  -0.0911   0.8688   0.0997
  -2.500   0.1300   0.03712   0.02756  -0.0931   0.8630   0.0975
  -2.250   0.1561   0.03549   0.02564  -0.0932   0.8538   0.0964
  -2.000   0.1912   0.03374   0.02350  -0.0947   0.8483   0.0955
  -1.750   0.2172   0.03256   0.02197  -0.0945   0.8391   0.0951
  -1.500   0.2525   0.03121   0.02023  -0.0957   0.8338   0.0952
  -1.250   0.2783   0.03039   0.01909  -0.0953   0.8246   0.0959
  -1.000   0.3139   0.02939   0.01771  -0.0965   0.8192   0.0973
  -0.750   0.3388   0.02886   0.01696  -0.0960   0.8104   0.0990
  -0.500   0.3703   0.02833   0.01638  -0.0967   0.8049   0.1067
  -0.250   0.3973   0.02817   0.01595  -0.0966   0.7971   0.1133
   0.000   0.4311   0.02767   0.01531  -0.0976   0.7913   0.1156
   0.250   0.4617   0.02736   0.01488  -0.0980   0.7851   0.1177
   0.500   0.4880   0.02724   0.01467  -0.0978   0.7777   0.1202
   0.750   0.5210   0.02693   0.01424  -0.0985   0.7734   0.1238
   1.000   0.5394   0.02723   0.01450  -0.0972   0.7650   0.1271
   1.250   0.5687   0.02709   0.01437  -0.0975   0.7601   0.1340
   1.500   0.5906   0.02730   0.01459  -0.0967   0.7528   0.1431
   1.750   0.6178   0.02720   0.01460  -0.0966   0.7462   0.1638
   2.000   0.6648   0.02536   0.01447  -0.1005   0.7402   1.0000
   2.500   0.7100   0.02597   0.01476  -0.0983   0.7217   1.0000
   2.750   0.7411   0.02586   0.01454  -0.0981   0.7140   1.0000
   3.000   0.7600   0.02624   0.01487  -0.0964   0.7029   1.0000
   3.250   0.7840   0.02639   0.01497  -0.0954   0.6932   1.0000
   3.500   0.8129   0.02633   0.01489  -0.0949   0.6850   1.0000
   3.750   0.8317   0.02680   0.01539  -0.0934   0.6750   1.0000
   4.000   0.8628   0.02672   0.01531  -0.0933   0.6687   1.0000
   4.250   0.8801   0.02728   0.01596  -0.0917   0.6584   1.0000
   4.500   0.9041   0.02754   0.01628  -0.0908   0.6500   1.0000
   4.750   0.9302   0.02768   0.01649  -0.0900   0.6414   1.0000
   5.000   0.9502   0.02808   0.01700  -0.0886   0.6306   1.0000
   5.250   0.9758   0.02814   0.01715  -0.0877   0.6199   1.0000
   5.500   1.0058   0.02792   0.01700  -0.0871   0.6089   1.0000
   5.750   1.0278   0.02806   0.01726  -0.0856   0.5952   1.0000
   6.000   1.0494   0.02823   0.01757  -0.0840   0.5808   1.0000
   6.250   1.0705   0.02844   0.01791  -0.0825   0.5662   1.0000
   6.500   1.0913   0.02867   0.01828  -0.0809   0.5511   1.0000
   6.750   1.1116   0.02891   0.01866  -0.0792   0.5353   1.0000
   7.000   1.1309   0.02923   0.01917  -0.0774   0.5194   1.0000
   7.250   1.1492   0.02963   0.01975  -0.0756   0.5034   1.0000
   7.500   1.1658   0.03010   0.02040  -0.0736   0.4868   1.0000
   7.750   1.1758   0.03084   0.02135  -0.0709   0.4674   1.0000
   8.000   1.1878   0.03144   0.02214  -0.0684   0.4476   1.0000
   8.250   1.2023   0.03184   0.02273  -0.0661   0.4279   1.0000
   8.500   1.2118   0.03254   0.02359  -0.0633   0.4066   1.0000
   8.750   1.2262   0.03295   0.02409  -0.0608   0.3871   1.0000
   9.000   1.2396   0.03349   0.02468  -0.0583   0.3672   1.0000
   9.250   1.2480   0.03420   0.02525  -0.0552   0.3412   1.0000
   9.500   1.2466   0.03553   0.02637  -0.0514   0.3099   1.0000
   9.750   1.2398   0.03737   0.02810  -0.0479   0.2778   1.0000
  10.000   1.2314   0.03954   0.03031  -0.0449   0.2449   1.0000
  10.250   1.2241   0.04195   0.03271  -0.0427   0.2094   1.0000
  10.500   1.2178   0.04459   0.03525  -0.0408   0.1703   1.0000
  10.750   1.2083   0.04772   0.03807  -0.0392   0.1419   1.0000
  11.000   1.1968   0.05137   0.04140  -0.0378   0.1229   1.0000
  11.250   1.1886   0.05500   0.04498  -0.0367   0.1043   1.0000
  11.500   1.1823   0.05865   0.04873  -0.0358   0.0851   1.0000
  11.750   1.1767   0.06231   0.05239  -0.0353   0.0716   1.0000
  12.000   1.1725   0.06588   0.05596  -0.0350   0.0640   1.0000
  12.250   1.1677   0.06958   0.05963  -0.0347   0.0594   1.0000
  12.500   1.1653   0.07308   0.06323  -0.0344   0.0546   1.0000
  12.750   1.1614   0.07676   0.06690  -0.0343   0.0512   1.0000
  13.000   1.1635   0.07985   0.07020  -0.0338   0.0476   1.0000
  13.250   1.1653   0.08300   0.07352  -0.0334   0.0446   1.0000
  13.500   1.1680   0.08605   0.07667  -0.0329   0.0426   1.0000
  13.750   1.1724   0.08887   0.07951  -0.0322   0.0407   1.0000
  14.000   1.1753   0.09238   0.08337  -0.0321   0.0387   1.0000
  14.250   1.1754   0.09623   0.08747  -0.0325   0.0371   1.0000
  14.500   1.1746   0.10018   0.09160  -0.0331   0.0358   1.0000
  14.750   1.1746   0.10396   0.09560  -0.0337   0.0347   1.0000
  15.000   1.1709   0.10872   0.10057  -0.0350   0.0340   1.0000
  15.250   1.1620   0.11464   0.10679  -0.0372   0.0337   1.0000
  15.500   1.1517   0.12099   0.11339  -0.0401   0.0337   1.0000
  15.750   1.1384   0.12827   0.12091  -0.0438   0.0336   1.0000
  16.000   1.1249   0.13601   0.12886  -0.0481   0.0337   1.0000
  16.250   1.1105   0.14449   0.13751  -0.0531   0.0339   1.0000
  16.500   1.0969   0.15333   0.14638  -0.0583   0.0341   1.0000
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