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GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 591 AIRFOIL (goe591-il)
Reynolds number: 50,000
Max Cl/Cd: 34.41 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe591-il-50000-n5.txt
Download as CSV file: xf-goe591-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 591 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3274   0.10943   0.10337  -0.0329   1.0000   0.1165
  -8.000  -0.3485   0.10890   0.10299  -0.0305   1.0000   0.1167
  -7.750  -0.3698   0.10825   0.10248  -0.0282   1.0000   0.1169
  -7.500  -0.3863   0.10687   0.10120  -0.0279   0.9997   0.1171
  -7.250  -0.3648   0.10137   0.09571  -0.0287   0.9951   0.1184
  -6.750  -0.3259   0.09302   0.08730  -0.0344   0.9808   0.1261
  -6.250  -0.2936   0.07612   0.06999  -0.0585   0.9573   0.0722
  -6.000  -0.2722   0.07174   0.06552  -0.0619   0.9500   0.0710
  -5.750  -0.2550   0.06727   0.06092  -0.0655   0.9402   0.0705
  -5.500  -0.2288   0.06153   0.05483  -0.0722   0.9325   0.0717
  -5.250  -0.2088   0.05685   0.04979  -0.0756   0.9226   0.0721
  -5.000  -0.1834   0.05245   0.04500  -0.0787   0.9150   0.0720
  -4.750  -0.1581   0.04839   0.04047  -0.0812   0.9066   0.0722
  -4.500  -0.1324   0.04572   0.03759  -0.0827   0.8988   0.0746
  -4.250  -0.1037   0.04359   0.03524  -0.0842   0.8911   0.0777
  -4.000  -0.0761   0.04084   0.03203  -0.0854   0.8829   0.0789
  -3.750  -0.0430   0.03816   0.02881  -0.0872   0.8760   0.0801
  -3.500  -0.0145   0.03610   0.02627  -0.0877   0.8677   0.0818
  -3.250   0.0217   0.03422   0.02374  -0.0893   0.8612   0.0865
  -3.000   0.0494   0.03293   0.02228  -0.0895   0.8525   0.0902
  -2.750   0.0863   0.03154   0.02062  -0.0909   0.8462   0.0939
  -2.500   0.1152   0.03052   0.01931  -0.0909   0.8374   0.0982
  -2.250   0.1535   0.02934   0.01788  -0.0923   0.8312   0.1041
  -2.000   0.1812   0.02878   0.01719  -0.0921   0.8218   0.1148
  -1.750   0.2193   0.02795   0.01626  -0.0935   0.8156   0.1326
  -1.500   0.2454   0.02747   0.01581  -0.0931   0.8056   0.1523
  -1.250   0.2822   0.02679   0.01520  -0.0944   0.7995   0.1989
  -1.000   0.3053   0.02633   0.01494  -0.0937   0.7888   0.2516
  -0.750   0.3400   0.02510   0.01430  -0.0948   0.7831   0.3708
  -0.500   0.3892   0.02351   0.01409  -0.0979   0.7740   1.0000
  -0.250   0.4256   0.02342   0.01358  -0.0989   0.7674   1.0000
   0.000   0.4458   0.02373   0.01364  -0.0975   0.7555   1.0000
   0.250   0.4707   0.02392   0.01359  -0.0968   0.7454   1.0000
   0.500   0.5024   0.02393   0.01335  -0.0971   0.7376   1.0000
   0.750   0.5232   0.02426   0.01351  -0.0958   0.7262   1.0000
   1.000   0.5512   0.02438   0.01344  -0.0956   0.7174   1.0000
   1.250   0.5776   0.02454   0.01346  -0.0951   0.7081   1.0000
   1.500   0.5995   0.02487   0.01367  -0.0940   0.6974   1.0000
   1.750   0.6328   0.02481   0.01345  -0.0945   0.6905   1.0000
   2.000   0.6516   0.02526   0.01383  -0.0930   0.6791   1.0000
   2.250   0.6754   0.02556   0.01403  -0.0922   0.6694   1.0000
   2.500   0.7051   0.02562   0.01399  -0.0922   0.6614   1.0000
   2.750   0.7247   0.02609   0.01442  -0.0909   0.6506   1.0000
   3.000   0.7528   0.02622   0.01448  -0.0906   0.6424   1.0000
   3.250   0.7763   0.02654   0.01477  -0.0898   0.6326   1.0000
   3.500   0.7975   0.02697   0.01517  -0.0887   0.6226   1.0000
   3.750   0.8291   0.02695   0.01509  -0.0889   0.6150   1.0000
   4.000   0.8465   0.02754   0.01569  -0.0873   0.6039   1.0000
   4.250   0.8705   0.02785   0.01600  -0.0865   0.5946   1.0000
   4.500   0.8976   0.02802   0.01616  -0.0861   0.5858   1.0000
   4.750   0.9157   0.02859   0.01676  -0.0847   0.5751   1.0000
   5.000   0.9433   0.02875   0.01693  -0.0843   0.5665   1.0000
   5.250   0.9644   0.02920   0.01742  -0.0832   0.5565   1.0000
   5.500   0.9834   0.02976   0.01804  -0.0819   0.5464   1.0000
   5.750   1.0147   0.02979   0.01808  -0.0820   0.5385   1.0000
   6.000   1.0281   0.03061   0.01901  -0.0800   0.5276   1.0000
   6.250   1.0498   0.03110   0.01956  -0.0790   0.5184   1.0000
   6.500   1.0751   0.03141   0.01994  -0.0785   0.5094   1.0000
   6.750   1.0890   0.03224   0.02090  -0.0766   0.4990   1.0000
   7.000   1.1152   0.03254   0.02125  -0.0761   0.4904   1.0000
   7.250   1.1320   0.03324   0.02206  -0.0746   0.4802   1.0000
   7.500   1.1467   0.03405   0.02302  -0.0728   0.4700   1.0000
   7.750   1.1762   0.03418   0.02321  -0.0727   0.4613   1.0000
   8.000   1.1854   0.03518   0.02436  -0.0703   0.4501   1.0000
   8.250   1.1979   0.03598   0.02528  -0.0682   0.4389   1.0000
   8.500   1.2174   0.03636   0.02575  -0.0668   0.4278   1.0000
   8.750   1.2385   0.03665   0.02614  -0.0655   0.4165   1.0000
   9.000   1.2396   0.03786   0.02751  -0.0622   0.4050   1.0000
   9.250   1.2482   0.03881   0.02858  -0.0598   0.3944   1.0000
   9.500   1.2700   0.03916   0.02901  -0.0587   0.3846   1.0000
   9.750   1.2699   0.04065   0.03068  -0.0557   0.3742   1.0000
  10.000   1.2752   0.04198   0.03220  -0.0533   0.3645   1.0000
  10.250   1.2978   0.04229   0.03261  -0.0524   0.3552   1.0000
  10.500   1.2894   0.04453   0.03505  -0.0493   0.3453   1.0000
  10.750   1.2956   0.04595   0.03663  -0.0474   0.3362   1.0000
  11.000   1.3110   0.04675   0.03756  -0.0461   0.3271   1.0000
  11.250   1.2995   0.04960   0.04060  -0.0436   0.3178   1.0000
  11.500   1.3065   0.05088   0.04200  -0.0420   0.3077   1.0000
  11.750   1.3163   0.05161   0.04283  -0.0404   0.2961   1.0000
  12.000   1.3001   0.05526   0.04667  -0.0387   0.2864   1.0000
  12.250   1.2947   0.05777   0.04929  -0.0374   0.2752   1.0000
  12.500   1.2952   0.05963   0.05123  -0.0362   0.2635   1.0000
  12.750   1.2954   0.06150   0.05313  -0.0351   0.2510   1.0000
  13.000   1.2805   0.06583   0.05765  -0.0349   0.2413   1.0000
  13.250   1.2728   0.06934   0.06129  -0.0347   0.2313   1.0000
  13.500   1.2717   0.07185   0.06388  -0.0343   0.2200   1.0000
  13.750   1.2654   0.07511   0.06720  -0.0343   0.2075   1.0000
  14.000   1.2444   0.08134   0.07364  -0.0358   0.1983   1.0000
  14.250   1.2312   0.08626   0.07866  -0.0370   0.1859   1.0000
  14.500   1.2188   0.09130   0.08378  -0.0384   0.1731   1.0000
  14.750   1.2064   0.09656   0.08913  -0.0401   0.1596   1.0000
  15.000   1.1958   0.10167   0.09432  -0.0418   0.1455   1.0000
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