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GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 611 AIRFOIL (goe611-il)
Reynolds number: 50,000
Max Cl/Cd: 31.23 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe611-il-50000-n5.txt
Download as CSV file: xf-goe611-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 611 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2831   0.13402   0.12787  -0.0402   1.0000   0.0757
  -9.750  -0.2992   0.13384   0.12782  -0.0386   1.0000   0.0760
  -9.500  -0.3160   0.13359   0.12770  -0.0368   1.0000   0.0761
  -9.250  -0.2993   0.12705   0.12119  -0.0340   1.0000   0.0779
  -9.000  -0.2981   0.12430   0.11849  -0.0314   1.0000   0.0799
  -8.750  -0.2836   0.12044   0.11463  -0.0342   0.9952   0.0834
  -8.500  -0.2722   0.11695   0.11113  -0.0385   0.9884   0.0874
  -8.250  -0.2717   0.11487   0.10908  -0.0451   0.9787   0.0907
  -8.000  -0.2740   0.11287   0.10714  -0.0537   0.9661   0.0917
  -7.750  -0.2423   0.10603   0.10026  -0.0495   0.9657   0.0969
  -7.500  -0.2319   0.10275   0.09700  -0.0531   0.9576   0.1032
  -7.250  -0.2340   0.10063   0.09486  -0.0643   0.9417   0.1076
  -7.000  -0.2126   0.09533   0.08961  -0.0607   0.9384   0.1128
  -6.750  -0.2013   0.09207   0.08633  -0.0647   0.9290   0.1206
  -6.250  -0.1738   0.08458   0.07881  -0.0707   0.9125   0.1327
  -5.500  -0.1296   0.07491   0.06885  -0.0827   0.8859   0.1721
  -5.250  -0.1096   0.07089   0.06487  -0.0835   0.8803   0.1913
  -5.000  -0.0954   0.06807   0.06207  -0.0823   0.8724   0.2120
  -4.750  -0.0294   0.05975   0.05241  -0.0984   0.8648   0.0915
  -4.500  -0.0033   0.05526   0.04765  -0.0996   0.8573   0.0750
  -4.000   0.0564   0.04868   0.04043  -0.1033   0.8446   0.0731
  -3.750   0.0822   0.04612   0.03752  -0.1040   0.8362   0.0720
  -3.500   0.1211   0.04309   0.03399  -0.1064   0.8320   0.0701
  -3.250   0.1436   0.04149   0.03199  -0.1058   0.8218   0.0713
  -3.000   0.1825   0.03937   0.02930  -0.1076   0.8171   0.0733
  -2.750   0.2064   0.03805   0.02762  -0.1069   0.8074   0.0732
  -2.500   0.2438   0.03634   0.02547  -0.1082   0.8021   0.0737
  -2.250   0.2691   0.03570   0.02440  -0.1074   0.7926   0.0762
  -2.000   0.3038   0.03410   0.02264  -0.1084   0.7868   0.0785
  -1.750   0.3291   0.03337   0.02172  -0.1077   0.7776   0.0794
  -1.500   0.3624   0.03241   0.02057  -0.1080   0.7714   0.0810
  -1.250   0.3871   0.03202   0.02003  -0.1072   0.7621   0.0834
  -1.000   0.4203   0.03136   0.01915  -0.1076   0.7557   0.0889
  -0.750   0.4427   0.03125   0.01886  -0.1066   0.7459   0.0918
  -0.500   0.4756   0.03053   0.01806  -0.1071   0.7399   0.0955
  -0.250   0.4965   0.03054   0.01797  -0.1060   0.7296   0.0998
   0.000   0.5306   0.03003   0.01729  -0.1067   0.7239   0.1075
   0.250   0.5504   0.03013   0.01742  -0.1056   0.7133   0.1218
   0.500   0.5851   0.02729   0.01699  -0.1061   0.7084   1.0000
   0.750   0.6032   0.02786   0.01725  -0.1044   0.6977   1.0000
   1.000   0.6378   0.02771   0.01671  -0.1050   0.6924   1.0000
   1.250   0.6542   0.02836   0.01718  -0.1034   0.6814   1.0000
   1.500   0.6813   0.02854   0.01714  -0.1032   0.6741   1.0000
   1.750   0.7046   0.02889   0.01732  -0.1025   0.6654   1.0000
   2.000   0.7283   0.02924   0.01753  -0.1019   0.6572   1.0000
   2.250   0.7543   0.02947   0.01761  -0.1015   0.6495   1.0000
   2.500   0.7759   0.02994   0.01799  -0.1007   0.6409   1.0000
   3.000   0.8233   0.03068   0.01854  -0.0995   0.6251   1.0000
   3.250   0.8518   0.03080   0.01858  -0.0995   0.6183   1.0000
   3.500   0.8702   0.03148   0.01922  -0.0983   0.6094   1.0000
   3.750   0.8989   0.03160   0.01927  -0.0983   0.6028   1.0000
   4.000   0.9162   0.03235   0.02003  -0.0970   0.5939   1.0000
   4.250   0.9447   0.03250   0.02013  -0.0971   0.5875   1.0000
   4.500   0.9612   0.03331   0.02096  -0.0957   0.5787   1.0000
   4.750   0.9891   0.03349   0.02113  -0.0957   0.5721   1.0000
   5.000   1.0049   0.03437   0.02205  -0.0943   0.5636   1.0000
   5.250   1.0326   0.03452   0.02219  -0.0941   0.5566   1.0000
   5.500   1.0466   0.03542   0.02314  -0.0925   0.5474   1.0000
   5.750   1.0774   0.03535   0.02309  -0.0926   0.5404   1.0000
   6.000   1.0867   0.03649   0.02430  -0.0904   0.5306   1.0000
   6.250   1.1225   0.03608   0.02388  -0.0911   0.5239   1.0000
   6.500   1.1259   0.03750   0.02543  -0.0882   0.5133   1.0000
   6.750   1.1600   0.03714   0.02507  -0.0886   0.5062   1.0000
   7.000   1.1638   0.03845   0.02650  -0.0857   0.4958   1.0000
   7.250   1.1778   0.03918   0.02729  -0.0839   0.4871   1.0000
   7.500   1.1970   0.03964   0.02786  -0.0827   0.4789   1.0000
   7.750   1.1990   0.04117   0.02951  -0.0799   0.4697   1.0000
   8.000   1.2264   0.04113   0.02954  -0.0796   0.4623   1.0000
   8.250   1.2187   0.04336   0.03191  -0.0761   0.4522   1.0000
   8.500   1.2567   0.04248   0.03111  -0.0765   0.4453   1.0000
   8.750   1.2399   0.04539   0.03418  -0.0726   0.4342   1.0000
   9.000   1.2462   0.04670   0.03561  -0.0706   0.4244   1.0000
   9.250   1.2699   0.04651   0.03551  -0.0697   0.4153   1.0000
   9.500   1.2560   0.04960   0.03874  -0.0668   0.4038   1.0000
   9.750   1.2604   0.05121   0.04048  -0.0651   0.3937   1.0000
  10.000   1.2786   0.05155   0.04096  -0.0640   0.3851   1.0000
  10.250   1.2636   0.05531   0.04489  -0.0621   0.3739   1.0000
  10.500   1.2722   0.05670   0.04641  -0.0608   0.3648   1.0000
  10.750   1.2807   0.05811   0.04795  -0.0596   0.3554   1.0000
  11.000   1.2674   0.06209   0.05210  -0.0584   0.3440   1.0000
  11.250   1.2729   0.06393   0.05408  -0.0573   0.3343   1.0000
  11.500   1.2868   0.06470   0.05501  -0.0562   0.3250   1.0000
  11.750   1.2734   0.06898   0.05944  -0.0555   0.3129   1.0000
  12.000   1.2700   0.07210   0.06269  -0.0548   0.3017   1.0000
  12.250   1.2908   0.07182   0.06251  -0.0535   0.2924   1.0000
  12.500   1.2899   0.07437   0.06515  -0.0528   0.2796   1.0000
  12.750   1.2781   0.07872   0.06961  -0.0526   0.2668   1.0000
  13.000   1.2718   0.08234   0.07331  -0.0524   0.2543   1.0000
  13.250   1.2706   0.08517   0.07619  -0.0521   0.2418   1.0000
  13.500   1.2759   0.08702   0.07806  -0.0516   0.2305   1.0000
  13.750   1.2702   0.09101   0.08220  -0.0519   0.2212   1.0000
  14.000   1.2660   0.09478   0.08607  -0.0522   0.2123   1.0000
  14.250   1.2693   0.09707   0.08836  -0.0522   0.2016   1.0000
  14.500   1.2586   0.10217   0.09361  -0.0533   0.1930   1.0000
  14.750   1.2570   0.10565   0.09717  -0.0539   0.1851   1.0000
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