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GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 498 AIRFOIL (goe498-il)
Reynolds number: 50,000
Max Cl/Cd: 24.75 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe498-il-50000-n5.txt
Download as CSV file: xf-goe498-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 498 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3091   0.12374   0.11620  -0.0419   1.0000   0.1003
 -10.500  -0.3184   0.12116   0.11369  -0.0412   1.0000   0.1002
 -10.000  -0.3514   0.11456   0.10723  -0.0408   1.0000   0.0989
  -9.750  -0.3504   0.11060   0.10330  -0.0431   0.9968   0.0989
  -9.500  -0.3259   0.10832   0.10101  -0.0454   0.9913   0.1009
  -9.250  -0.3123   0.10459   0.09727  -0.0492   0.9846   0.1026
  -9.000  -0.3047   0.10008   0.09274  -0.0536   0.9775   0.1038
  -8.750  -0.3003   0.09500   0.08765  -0.0586   0.9700   0.1045
  -8.500  -0.3034   0.08986   0.08251  -0.0628   0.9603   0.1054
  -8.250  -0.3161   0.08373   0.07638  -0.0679   0.9497   0.1067
  -8.000  -0.3615   0.07034   0.06289  -0.0805   0.9340   0.1078
  -7.750  -0.3890   0.05671   0.04871  -0.0954   0.9206   0.1096
  -7.500  -0.3715   0.05533   0.04731  -0.0957   0.9114   0.1119
  -7.250  -0.3492   0.05100   0.04263  -0.1012   0.9052   0.1157
  -7.000  -0.3439   0.04600   0.03693  -0.1045   0.8942   0.1196
  -6.750  -0.3129   0.04509   0.03606  -0.1058   0.8885   0.1230
  -6.500  -0.2907   0.04343   0.03418  -0.1068   0.8808   0.1273
  -6.250  -0.2674   0.04105   0.03133  -0.1086   0.8729   0.1324
  -6.000  -0.2338   0.04028   0.03060  -0.1101   0.8679   0.1373
  -5.750  -0.2141   0.03898   0.02898  -0.1101   0.8591   0.1430
  -5.500  -0.1861   0.03799   0.02790  -0.1109   0.8522   0.1485
  -5.000  -0.1332   0.03627   0.02589  -0.1117   0.8382   0.1626
  -4.750  -0.1026   0.03559   0.02515  -0.1125   0.8320   0.1713
  -4.500  -0.0653   0.03473   0.02424  -0.1143   0.8280   0.1818
  -4.250  -0.0507   0.03442   0.02378  -0.1127   0.8176   0.1917
  -4.000  -0.0180   0.03394   0.02337  -0.1135   0.8122   0.2045
  -3.750   0.0113   0.03357   0.02300  -0.1139   0.8061   0.2187
  -3.500   0.0322   0.03346   0.02287  -0.1130   0.7972   0.2329
  -3.250   0.0679   0.03309   0.02246  -0.1142   0.7926   0.2513
  -3.000   0.0889   0.03312   0.02243  -0.1133   0.7840   0.2671
  -2.750   0.1176   0.03297   0.02221  -0.1134   0.7772   0.2848
  -2.500   0.1547   0.03269   0.02191  -0.1146   0.7732   0.3059
  -2.250   0.1693   0.03308   0.02229  -0.1127   0.7631   0.3230
  -2.000   0.2008   0.03296   0.02217  -0.1131   0.7573   0.3450
  -1.750   0.2397   0.03259   0.02179  -0.1143   0.7537   0.3660
  -1.500   0.2495   0.03303   0.02228  -0.1117   0.7425   0.3767
  -1.250   0.2848   0.03271   0.02189  -0.1125   0.7373   0.3946
  -1.000   0.3271   0.03224   0.02134  -0.1143   0.7339   0.4142
  -0.750   0.3339   0.03287   0.02200  -0.1113   0.7218   0.4252
  -0.500   0.3714   0.03253   0.02163  -0.1123   0.7169   0.4440
  -0.250   0.4013   0.03247   0.02154  -0.1123   0.7104   0.4617
   0.000   0.4188   0.03282   0.02187  -0.1108   0.7003   0.4784
   0.250   0.4587   0.03241   0.02145  -0.1120   0.6957   0.5007
   0.500   0.4719   0.03293   0.02200  -0.1098   0.6855   0.5178
   0.750   0.5016   0.03285   0.02193  -0.1096   0.6784   0.5413
   1.000   0.5430   0.03233   0.02144  -0.1109   0.6742   0.5684
   1.250   0.5466   0.03319   0.02237  -0.1076   0.6621   0.5865
   1.500   0.5812   0.03287   0.02209  -0.1080   0.6565   0.6142
   1.750   0.6243   0.03222   0.02149  -0.1095   0.6529   0.6465
   2.000   0.6199   0.03334   0.02274  -0.1051   0.6396   0.6682
   2.250   0.6563   0.03277   0.02230  -0.1056   0.6351   0.7102
   2.500   0.6597   0.03351   0.02326  -0.1021   0.6243   0.7541
   2.750   0.6897   0.03299   0.02301  -0.1017   0.6176   1.0000
   3.000   0.7374   0.03262   0.02242  -0.1044   0.6138   1.0000
   3.250   0.7331   0.03429   0.02404  -0.1009   0.6009   1.0000
   3.500   0.7739   0.03404   0.02363  -0.1023   0.5962   1.0000
   4.000   0.8085   0.03560   0.02505  -0.0999   0.5790   1.0000
   4.250   0.8527   0.03516   0.02449  -0.1016   0.5754   1.0000
   4.500   0.8407   0.03740   0.02675  -0.0974   0.5623   1.0000
   4.750   0.8806   0.03703   0.02630  -0.0983   0.5581   1.0000
   5.250   0.9086   0.03897   0.02820  -0.0952   0.5406   1.0000
   5.500   0.9498   0.03842   0.02759  -0.0962   0.5362   1.0000
   5.750   0.9361   0.04098   0.03020  -0.0923   0.5232   1.0000
   6.000   0.9844   0.03978   0.02893  -0.0935   0.5190   1.0000
   6.250   0.9653   0.04283   0.03204  -0.0894   0.5056   1.0000
   6.500   1.0108   0.04161   0.03076  -0.0901   0.5008   1.0000
   6.750   0.9947   0.04464   0.03385  -0.0867   0.4879   1.0000
   7.000   1.0373   0.04341   0.03258  -0.0870   0.4824   1.0000
   7.250   1.0243   0.04632   0.03555  -0.0840   0.4699   1.0000
   7.500   1.0625   0.04531   0.03451  -0.0838   0.4640   1.0000
   7.750   1.0512   0.04823   0.03750  -0.0812   0.4519   1.0000
   8.000   1.0838   0.04765   0.03691  -0.0808   0.4458   1.0000
   8.250   1.0727   0.05086   0.04020  -0.0786   0.4347   1.0000
   8.500   1.0964   0.05105   0.04042  -0.0778   0.4282   1.0000
   8.750   1.1420   0.04944   0.03880  -0.0779   0.4247   1.0000
   9.000   1.1064   0.05498   0.04448  -0.0752   0.4108   1.0000
   9.250   1.1511   0.05316   0.04265  -0.0749   0.4071   1.0000
   9.500   1.1180   0.05890   0.04852  -0.0730   0.3931   1.0000
   9.750   1.1631   0.05674   0.04635  -0.0724   0.3893   1.0000
  10.000   1.1314   0.06267   0.05241  -0.0711   0.3751   1.0000
  10.250   1.1765   0.06032   0.05007  -0.0701   0.3715   1.0000
  10.500   1.1441   0.06666   0.05654  -0.0693   0.3570   1.0000
  10.750   1.1880   0.06428   0.05416  -0.0682   0.3535   1.0000
  11.000   1.1522   0.07147   0.06148  -0.0680   0.3389   1.0000
  11.250   1.1934   0.06928   0.05932  -0.0667   0.3355   1.0000
  11.500   1.1534   0.07751   0.06768  -0.0671   0.3207   1.0000
  11.750   1.1934   0.07525   0.06544  -0.0657   0.3175   1.0000
  12.250   1.1190   0.09291   0.08330  -0.0686   0.2906   1.0000
  12.500   1.1272   0.09527   0.08573  -0.0684   0.2847   1.0000
  12.750   1.1603   0.09348   0.08398  -0.0668   0.2821   1.0000
  13.250   1.1096   0.10935   0.10000  -0.0711   0.2610   1.0000
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