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GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 359 AIRFOIL (goe359-il)
Reynolds number: 50,000
Max Cl/Cd: 41.45 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe359-il-50000-n5.txt
Download as CSV file: xf-goe359-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 359 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2609   0.10120   0.09522  -0.0274   1.0000   0.0692
  -7.000  -0.2655   0.09965   0.09382  -0.0267   1.0000   0.0714
  -6.750  -0.2729   0.09878   0.09310  -0.0268   1.0000   0.0735
  -6.500  -0.2823   0.09849   0.09296  -0.0277   1.0000   0.0745
  -6.250  -0.2893   0.09809   0.09266  -0.0293   1.0000   0.0749
  -6.000  -0.2904   0.09353   0.08821  -0.0228   1.0000   0.0778
  -5.750  -0.2671   0.09055   0.08521  -0.0300   0.9918   0.0863
  -5.500  -0.2404   0.08569   0.08031  -0.0355   0.9818   0.0907
  -5.250  -0.1937   0.08270   0.07714  -0.0508   0.9677   0.1013
  -5.000  -0.1785   0.07724   0.07175  -0.0494   0.9588   0.1048
  -4.500  -0.1128   0.06923   0.06357  -0.0617   0.9370   0.1272
  -4.250  -0.0748   0.06530   0.05952  -0.0690   0.9268   0.1436
  -4.000  -0.0428   0.06116   0.05528  -0.0735   0.9161   0.1520
  -3.750   0.0005   0.05713   0.05105  -0.0810   0.9073   0.1643
  -3.250   0.1165   0.04626   0.03903  -0.0999   0.8889   0.0871
  -3.000   0.1562   0.04240   0.03495  -0.1038   0.8814   0.0817
  -2.750   0.1948   0.03951   0.03163  -0.1072   0.8702   0.0837
  -2.500   0.2338   0.03674   0.02842  -0.1102   0.8600   0.0832
  -2.250   0.2760   0.03397   0.02513  -0.1133   0.8519   0.0806
  -2.000   0.3107   0.03191   0.02255  -0.1147   0.8402   0.0791
  -1.750   0.3447   0.03020   0.02035  -0.1158   0.8292   0.0786
  -1.500   0.3783   0.02887   0.01864  -0.1167   0.8188   0.0806
  -1.250   0.4120   0.02785   0.01717  -0.1173   0.8085   0.0863
  -1.000   0.4413   0.02697   0.01589  -0.1173   0.7965   0.0874
  -0.750   0.4703   0.02618   0.01482  -0.1170   0.7852   0.0878
  -0.500   0.5014   0.02545   0.01382  -0.1170   0.7749   0.0889
  -0.250   0.5314   0.02489   0.01303  -0.1169   0.7643   0.0905
   0.000   0.5587   0.02454   0.01253  -0.1165   0.7527   0.0928
   0.250   0.5865   0.02425   0.01208  -0.1161   0.7418   0.0960
   0.500   0.6158   0.02396   0.01159  -0.1159   0.7324   0.1009
   0.750   0.6423   0.02382   0.01143  -0.1155   0.7213   0.1088
   1.000   0.6690   0.02371   0.01132  -0.1152   0.7106   0.1258
   1.250   0.6948   0.02238   0.01136  -0.1152   0.7019   0.4901
   1.500   0.7213   0.02201   0.01121  -0.1142   0.6915   1.0000
   1.750   0.7469   0.02238   0.01135  -0.1137   0.6812   1.0000
   2.000   0.7745   0.02264   0.01139  -0.1134   0.6725   1.0000
   2.250   0.8000   0.02302   0.01164  -0.1129   0.6625   1.0000
   2.500   0.8251   0.02343   0.01193  -0.1124   0.6526   1.0000
   2.750   0.8521   0.02366   0.01203  -0.1119   0.6432   1.0000
   3.000   0.8771   0.02392   0.01221  -0.1111   0.6314   1.0000
   3.250   0.9011   0.02420   0.01241  -0.1101   0.6183   1.0000
   3.500   0.9251   0.02447   0.01262  -0.1092   0.6054   1.0000
   3.750   0.9494   0.02476   0.01289  -0.1084   0.5933   1.0000
   4.000   0.9748   0.02503   0.01313  -0.1077   0.5828   1.0000
   4.250   0.9993   0.02539   0.01350  -0.1070   0.5725   1.0000
   4.500   1.0221   0.02588   0.01405  -0.1062   0.5616   1.0000
   4.750   1.0465   0.02628   0.01451  -0.1055   0.5516   1.0000
   5.000   1.0716   0.02660   0.01486  -0.1048   0.5418   1.0000
   5.250   1.0934   0.02715   0.01552  -0.1039   0.5304   1.0000
   5.500   1.1162   0.02763   0.01614  -0.1030   0.5196   1.0000
   5.750   1.1403   0.02800   0.01658  -0.1022   0.5091   1.0000
   6.000   1.1636   0.02842   0.01712  -0.1014   0.4981   1.0000
   6.250   1.1846   0.02902   0.01787  -0.1003   0.4861   1.0000
   6.500   1.2062   0.02957   0.01862  -0.0993   0.4744   1.0000
   6.750   1.2285   0.03007   0.01925  -0.0983   0.4628   1.0000
   7.000   1.2503   0.03050   0.01980  -0.0971   0.4500   1.0000
   7.250   1.2662   0.03077   0.02015  -0.0950   0.4289   1.0000
   7.500   1.2809   0.03090   0.02027  -0.0926   0.4051   1.0000
   7.750   1.2943   0.03147   0.02102  -0.0904   0.3843   1.0000
   8.000   1.3087   0.03206   0.02170  -0.0884   0.3658   1.0000
   8.250   1.3202   0.03281   0.02255  -0.0862   0.3451   1.0000
   8.500   1.3313   0.03365   0.02349  -0.0841   0.3257   1.0000
   8.750   1.3382   0.03461   0.02444  -0.0815   0.3016   1.0000
   9.000   1.3415   0.03579   0.02550  -0.0785   0.2776   1.0000
   9.250   1.3447   0.03720   0.02691  -0.0759   0.2579   1.0000
   9.500   1.3477   0.03882   0.02855  -0.0735   0.2408   1.0000
   9.750   1.3511   0.04058   0.03040  -0.0715   0.2267   1.0000
  10.000   1.3530   0.04260   0.03262  -0.0697   0.2119   1.0000
  10.250   1.3529   0.04496   0.03511  -0.0682   0.1940   1.0000
  10.500   1.3513   0.04766   0.03795  -0.0671   0.1695   1.0000
  10.750   1.3432   0.05113   0.04133  -0.0662   0.1335   1.0000
  11.250   1.3118   0.06057   0.05025  -0.0657   0.0649   1.0000
  11.500   1.2986   0.06543   0.05506  -0.0659   0.0562   1.0000
  11.750   1.2885   0.07005   0.05977  -0.0661   0.0479   1.0000
  12.000   1.2804   0.07457   0.06446  -0.0665   0.0392   1.0000
  12.250   1.2720   0.07923   0.06929  -0.0671   0.0349   1.0000
  12.500   1.2632   0.08405   0.07429  -0.0679   0.0328   1.0000
  12.750   1.2536   0.08913   0.07954  -0.0690   0.0314   1.0000
  13.000   1.2439   0.09437   0.08493  -0.0702   0.0305   1.0000
  13.250   1.2347   0.09968   0.09041  -0.0716   0.0299   1.0000
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