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GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 483 AIRFOIL (goe483-il)
Reynolds number: 500,000
Max Cl/Cd: 112.26 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe483-il-500000-n5.txt
Download as CSV file: xf-goe483-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 483 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.2812   0.14084   0.13867  -0.0175   1.0000   0.0047
 -12.750  -0.2755   0.13808   0.13592  -0.0186   1.0000   0.0048
  -7.250  -0.2155   0.08487   0.08277  -0.0405   0.9653   0.0074
  -7.000  -0.1900   0.08096   0.07883  -0.0468   0.9506   0.0077
  -6.750  -0.1641   0.07700   0.07483  -0.0533   0.9329   0.0082
  -6.500  -0.1426   0.07346   0.07122  -0.0584   0.9123   0.0084
  -6.000  -0.0879   0.05087   0.04847  -0.0560   0.8292   0.0106
  -5.000  -0.0310   0.05273   0.05002  -0.0802   0.8261   0.0061
  -4.750  -0.0061   0.04911   0.04630  -0.0842   0.8176   0.0059
  -4.500   0.0215   0.04535   0.04245  -0.0884   0.8099   0.0057
  -4.250   0.0520   0.04121   0.03818  -0.0929   0.8024   0.0055
  -4.000   0.0861   0.03638   0.03320  -0.0977   0.7955   0.0056
  -3.750   0.1238   0.03031   0.02688  -0.1030   0.7887   0.0058
  -3.500   0.1703   0.01549   0.01091  -0.1109   0.7840   0.0062
  -3.250   0.1987   0.01337   0.00827  -0.1113   0.7767   0.0067
  -3.000   0.2266   0.01146   0.00586  -0.1113   0.7697   0.0072
  -2.750   0.2541   0.01064   0.00479  -0.1112   0.7614   0.0079
  -2.500   0.2815   0.01006   0.00401  -0.1109   0.7523   0.0088
  -2.250   0.3088   0.00961   0.00338  -0.1106   0.7424   0.0102
  -2.000   0.3361   0.00909   0.00269  -0.1103   0.7318   0.0134
  -1.750   0.3634   0.00878   0.00230  -0.1100   0.7212   0.0183
  -1.500   0.3906   0.00859   0.00204  -0.1098   0.7103   0.0282
  -1.250   0.4176   0.00847   0.00184  -0.1095   0.6982   0.0364
  -1.000   0.4445   0.00837   0.00167  -0.1092   0.6849   0.0452
  -0.750   0.4714   0.00828   0.00152  -0.1090   0.6699   0.0550
  -0.500   0.4981   0.00821   0.00142  -0.1087   0.6528   0.0731
  -0.250   0.5246   0.00821   0.00137  -0.1083   0.6328   0.0915
   0.000   0.5511   0.00826   0.00130  -0.1080   0.6112   0.1019
   0.250   0.5773   0.00834   0.00126  -0.1076   0.5888   0.1106
   0.500   0.6036   0.00841   0.00126  -0.1073   0.5693   0.1202
   0.750   0.6299   0.00849   0.00128  -0.1070   0.5528   0.1325
   1.000   0.6564   0.00856   0.00132  -0.1068   0.5387   0.1512
   1.250   0.6829   0.00865   0.00140  -0.1065   0.5263   0.1743
   1.500   0.7094   0.00875   0.00148  -0.1063   0.5151   0.1938
   1.750   0.7361   0.00884   0.00155  -0.1060   0.5043   0.2068
   2.000   0.7628   0.00892   0.00163  -0.1058   0.4945   0.2170
   2.250   0.7894   0.00902   0.00171  -0.1056   0.4844   0.2265
   2.500   0.8159   0.00912   0.00181  -0.1054   0.4735   0.2365
   2.750   0.8424   0.00922   0.00192  -0.1052   0.4611   0.2477
   3.000   0.8688   0.00933   0.00203  -0.1049   0.4481   0.2615
   3.250   0.8951   0.00943   0.00217  -0.1047   0.4361   0.2779
   3.500   0.9213   0.00953   0.00231  -0.1045   0.4240   0.3053
   4.500   1.0249   0.00913   0.00306  -0.1035   0.3682   1.0000
   4.750   1.0489   0.00952   0.00331  -0.1030   0.3356   1.0000
   5.000   1.0722   0.01001   0.00361  -0.1024   0.2987   1.0000
   5.250   1.0935   0.01075   0.00405  -0.1015   0.2369   1.0000
   5.500   1.1098   0.01213   0.00482  -0.1001   0.1323   1.0000
   5.750   1.1227   0.01402   0.00608  -0.0981   0.0138   1.0000
   6.000   1.1456   0.01459   0.00675  -0.0973   0.0091   1.0000
   6.250   1.1692   0.01502   0.00725  -0.0967   0.0074   1.0000
   6.500   1.1914   0.01562   0.00795  -0.0958   0.0063   1.0000
   6.750   1.2115   0.01649   0.00895  -0.0946   0.0055   1.0000
   7.000   1.2320   0.01726   0.00982  -0.0935   0.0051   1.0000
   7.250   1.2528   0.01793   0.01055  -0.0925   0.0043   1.0000
   7.500   1.2721   0.01871   0.01138  -0.0914   0.0038   1.0000
   7.750   1.2863   0.01999   0.01278  -0.0894   0.0035   1.0000
   8.000   1.3014   0.02110   0.01401  -0.0875   0.0033   1.0000
   8.250   1.3139   0.02240   0.01548  -0.0853   0.0031   1.0000
   8.500   1.3244   0.02381   0.01702  -0.0828   0.0029   1.0000
   8.750   1.3333   0.02535   0.01869  -0.0801   0.0028   1.0000
   9.000   1.3400   0.02695   0.02041  -0.0771   0.0027   1.0000
   9.250   1.3474   0.02867   0.02225  -0.0742   0.0027   1.0000
   9.500   1.3561   0.03066   0.02438  -0.0717   0.0026   1.0000
   9.750   1.3667   0.03273   0.02660  -0.0696   0.0026   1.0000
  10.000   1.3738   0.03402   0.02800  -0.0675   0.0024   1.0000
  10.250   1.3800   0.03558   0.02968  -0.0654   0.0023   1.0000
  10.500   1.3832   0.03784   0.03207  -0.0634   0.0021   1.0000
  10.750   1.3888   0.04046   0.03498  -0.0612   0.0019   1.0000
  11.000   1.3919   0.04370   0.03849  -0.0591   0.0019   1.0000
  11.250   1.3907   0.04741   0.04249  -0.0569   0.0018   1.0000
  11.500   1.3858   0.05119   0.04653  -0.0550   0.0017   1.0000
  11.750   1.3778   0.05502   0.05060  -0.0535   0.0017   1.0000
  12.000   1.3663   0.05950   0.05534  -0.0524   0.0016   1.0000
  12.250   1.3537   0.06401   0.06007  -0.0520   0.0016   1.0000
  12.500   1.3397   0.06891   0.06518  -0.0523   0.0016   1.0000
  12.750   1.3249   0.07420   0.07067  -0.0533   0.0016   1.0000
  13.000   1.3085   0.08015   0.07682  -0.0550   0.0016   1.0000
  13.250   1.2925   0.08633   0.08317  -0.0575   0.0016   1.0000
  13.500   1.2755   0.09316   0.09018  -0.0607   0.0016   1.0000
  13.750   1.2597   0.10019   0.09738  -0.0645   0.0016   1.0000
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