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GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il)
Reynolds number: 50,000
Max Cl/Cd: 42.24 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe173-il-50000-n5.txt
Download as CSV file: xf-goe173-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 173 (ALBATROS 6020) 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  -0.2647   0.11285   0.10645  -0.0297   1.0000   0.0607
  -8.000  -0.2713   0.11224   0.10599  -0.0297   1.0000   0.0611
  -7.750  -0.2765   0.11146   0.10537  -0.0304   1.0000   0.0614
  -7.500  -0.2785   0.11041   0.10445  -0.0322   1.0000   0.0616
  -7.250  -0.2639   0.10250   0.09656  -0.0267   1.0000   0.0642
  -7.000  -0.2626   0.09997   0.09412  -0.0254   1.0000   0.0668
  -6.750  -0.2650   0.09814   0.09243  -0.0246   1.0000   0.0693
  -6.500  -0.2699   0.09678   0.09120  -0.0240   1.0000   0.0716
  -6.250  -0.2772   0.09606   0.09061  -0.0241   1.0000   0.0736
  -6.000  -0.2841   0.09588   0.09054  -0.0257   1.0000   0.0748
  -5.750  -0.2613   0.09107   0.08575  -0.0309   0.9924   0.0770
  -5.500  -0.2397   0.08643   0.08110  -0.0323   0.9848   0.0825
  -5.000  -0.1750   0.07818   0.07274  -0.0485   0.9628   0.0932
  -4.750  -0.1418   0.07433   0.06878  -0.0548   0.9535   0.1019
  -4.500  -0.1094   0.07024   0.06462  -0.0616   0.9424   0.1078
  -4.250  -0.0696   0.06689   0.06111  -0.0703   0.9314   0.1208
  -4.000  -0.0349   0.06309   0.05720  -0.0757   0.9233   0.1358
  -3.750  -0.0004   0.05957   0.05355  -0.0808   0.9138   0.1504
  -3.500   0.0333   0.05605   0.04989  -0.0851   0.9048   0.1652
  -3.250   0.0680   0.05222   0.04599  -0.0888   0.8979   0.1815
  -3.000   0.1393   0.04630   0.03927  -0.0997   0.8901   0.0879
  -2.750   0.1890   0.04203   0.03452  -0.1052   0.8838   0.0735
  -2.500   0.2268   0.03893   0.03110  -0.1083   0.8751   0.0700
  -2.250   0.2730   0.03608   0.02766  -0.1124   0.8688   0.0730
  -2.000   0.3100   0.03378   0.02489  -0.1145   0.8595   0.0727
  -1.750   0.3522   0.03147   0.02204  -0.1171   0.8525   0.0723
  -1.500   0.3893   0.02983   0.01983  -0.1184   0.8420   0.0765
  -1.250   0.4236   0.02832   0.01802  -0.1192   0.8299   0.0791
  -1.000   0.4586   0.02695   0.01625  -0.1196   0.8165   0.0800
  -0.750   0.4914   0.02584   0.01477  -0.1195   0.8022   0.0815
  -0.500   0.5234   0.02497   0.01352  -0.1191   0.7879   0.0837
  -0.250   0.5534   0.02435   0.01259  -0.1186   0.7745   0.0886
   0.000   0.5826   0.02383   0.01196  -0.1184   0.7622   0.0975
   0.250   0.6118   0.02340   0.01132  -0.1179   0.7500   0.1043
   0.500   0.6399   0.02303   0.01087  -0.1175   0.7371   0.1134
   0.750   0.6670   0.02276   0.01056  -0.1169   0.7234   0.1327
   1.000   0.6887   0.02071   0.01042  -0.1155   0.7100   1.0000
   1.250   0.7152   0.02091   0.01016  -0.1146   0.6958   1.0000
   1.500   0.7411   0.02110   0.01006  -0.1138   0.6812   1.0000
   1.750   0.7668   0.02130   0.01002  -0.1130   0.6662   1.0000
   2.000   0.7922   0.02150   0.01003  -0.1122   0.6509   1.0000
   2.250   0.8175   0.02170   0.01005  -0.1114   0.6351   1.0000
   2.500   0.8427   0.02190   0.01009  -0.1105   0.6189   1.0000
   2.750   0.8669   0.02215   0.01023  -0.1096   0.6016   1.0000
   3.000   0.8910   0.02242   0.01040  -0.1087   0.5837   1.0000
   3.250   0.9152   0.02270   0.01057  -0.1078   0.5658   1.0000
   3.500   0.9397   0.02299   0.01077  -0.1069   0.5482   1.0000
   3.750   0.9642   0.02331   0.01098  -0.1061   0.5312   1.0000
   4.000   0.9883   0.02370   0.01128  -0.1053   0.5144   1.0000
   4.250   1.0120   0.02415   0.01167  -0.1046   0.4978   1.0000
   4.500   1.0358   0.02463   0.01213  -0.1039   0.4825   1.0000
   4.750   1.0598   0.02513   0.01258  -0.1032   0.4689   1.0000
   5.000   1.0840   0.02566   0.01307  -0.1026   0.4569   1.0000
   5.250   1.1076   0.02629   0.01378  -0.1020   0.4453   1.0000
   5.500   1.1313   0.02693   0.01446  -0.1014   0.4352   1.0000
   5.750   1.1560   0.02751   0.01503  -0.1009   0.4268   1.0000
   6.000   1.1789   0.02826   0.01590  -0.1003   0.4176   1.0000
   6.250   1.2031   0.02894   0.01668  -0.0999   0.4102   1.0000
   6.500   1.2261   0.02973   0.01762  -0.0993   0.4029   1.0000
   6.750   1.2514   0.03045   0.01841  -0.0990   0.3975   1.0000
   7.000   1.2731   0.03143   0.01964  -0.0984   0.3913   1.0000
   7.250   1.2972   0.03225   0.02066  -0.0980   0.3860   1.0000
   7.500   1.3199   0.03320   0.02182  -0.0975   0.3807   1.0000
   7.750   1.3408   0.03427   0.02316  -0.0968   0.3751   1.0000
   8.000   1.3651   0.03517   0.02426  -0.0964   0.3707   1.0000
   8.250   1.3846   0.03636   0.02582  -0.0955   0.3654   1.0000
   8.500   1.4032   0.03676   0.02633  -0.0940   0.3524   1.0000
   8.750   1.4175   0.03723   0.02692  -0.0919   0.3375   1.0000
   9.000   1.4265   0.03778   0.02762  -0.0893   0.3202   1.0000
   9.250   1.4327   0.03842   0.02840  -0.0863   0.3028   1.0000
   9.500   1.4413   0.03929   0.02950  -0.0839   0.2902   1.0000
   9.750   1.4464   0.04026   0.03070  -0.0811   0.2771   1.0000
  10.000   1.4497   0.04133   0.03206  -0.0781   0.2649   1.0000
  10.250   1.4425   0.04283   0.03379  -0.0744   0.2498   1.0000
  10.500   1.4347   0.04481   0.03604  -0.0715   0.2335   1.0000
  10.750   1.4229   0.04750   0.03895  -0.0693   0.2092   1.0000
  11.000   1.4112   0.05092   0.04253  -0.0682   0.1589   1.0000
  11.250   1.3881   0.05557   0.04650  -0.0674   0.1107   1.0000
  11.500   1.3665   0.06116   0.05187  -0.0676   0.0835   1.0000
  11.750   1.3455   0.06718   0.05784  -0.0684   0.0659   1.0000
  12.000   1.3269   0.07325   0.06399  -0.0695   0.0579   1.0000
  12.250   1.3091   0.07948   0.07035  -0.0710   0.0531   1.0000
  12.500   1.2915   0.08590   0.07691  -0.0728   0.0502   1.0000
  12.750   1.2754   0.09227   0.08343  -0.0747   0.0475   1.0000
  13.000   1.2601   0.09864   0.08995  -0.0766   0.0452   1.0000
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