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GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il)
Reynolds number: 100,000
Max Cl/Cd: 60.3 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe173-il-100000-n5.txt
Download as CSV file: xf-goe173-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2688   0.11127   0.10679  -0.0309   1.0000   0.0270
  -8.000  -0.2714   0.10943   0.10504  -0.0303   1.0000   0.0270
  -7.500  -0.2727   0.10537   0.10115  -0.0306   1.0000   0.0271
  -7.250  -0.2660   0.09899   0.09481  -0.0260   1.0000   0.0278
  -7.000  -0.2658   0.09621   0.09210  -0.0238   1.0000   0.0285
  -6.750  -0.2505   0.09260   0.08852  -0.0267   0.9950   0.0296
  -6.500  -0.2244   0.08831   0.08423  -0.0331   0.9857   0.0309
  -6.250  -0.1979   0.08412   0.08003  -0.0398   0.9747   0.0320
  -6.000  -0.1702   0.07997   0.07586  -0.0468   0.9624   0.0333
  -5.750  -0.1378   0.07588   0.07172  -0.0554   0.9491   0.0350
  -5.500  -0.0896   0.07194   0.06765  -0.0697   0.9347   0.0364
  -5.250  -0.0481   0.06766   0.06319  -0.0791   0.9234   0.0367
  -5.000  -0.0297   0.06236   0.05793  -0.0808   0.9127   0.0375
  -4.750  -0.0134   0.05902   0.05460  -0.0805   0.9016   0.0404
  -4.500   0.0503   0.05578   0.05095  -0.0945   0.8898   0.0483
  -4.250   0.0695   0.05078   0.04601  -0.0958   0.8806   0.0502
  -4.000   0.0967   0.04767   0.04283  -0.0980   0.8698   0.0540
  -3.750   0.1482   0.04396   0.03866  -0.1065   0.8589   0.0626
  -3.500   0.1702   0.04106   0.03578  -0.1071   0.8484   0.0676
  -3.000   0.2543   0.03259   0.02644  -0.1151   0.8271   0.0443
  -2.750   0.2900   0.02954   0.02294  -0.1172   0.8146   0.0440
  -2.500   0.3251   0.02688   0.01974  -0.1186   0.8018   0.0457
  -2.250   0.3580   0.02454   0.01688  -0.1195   0.7887   0.0454
  -2.000   0.3907   0.02306   0.01474  -0.1198   0.7758   0.0486
  -1.750   0.4203   0.02131   0.01259  -0.1200   0.7628   0.0494
  -1.250   0.4769   0.01930   0.00999  -0.1197   0.7361   0.0530
  -1.000   0.5045   0.01866   0.00915  -0.1194   0.7236   0.0562
  -0.750   0.5320   0.01799   0.00826  -0.1190   0.7120   0.0566
  -0.500   0.5593   0.01744   0.00755  -0.1186   0.7006   0.0572
  -0.250   0.5863   0.01699   0.00698  -0.1181   0.6895   0.0582
   0.000   0.6129   0.01665   0.00652  -0.1176   0.6780   0.0596
   0.250   0.6391   0.01641   0.00616  -0.1171   0.6655   0.0613
   0.500   0.6655   0.01619   0.00587  -0.1166   0.6530   0.0656
   0.750   0.6922   0.01611   0.00568  -0.1162   0.6403   0.0746
   1.000   0.7190   0.01599   0.00550  -0.1158   0.6271   0.0839
   1.250   0.7457   0.01581   0.00542  -0.1154   0.6136   0.1336
   1.750   0.7932   0.01438   0.00537  -0.1135   0.5855   1.0000
   2.000   0.8189   0.01456   0.00537  -0.1129   0.5695   1.0000
   2.250   0.8444   0.01476   0.00540  -0.1123   0.5524   1.0000
   2.500   0.8696   0.01498   0.00547  -0.1117   0.5342   1.0000
   2.750   0.8945   0.01523   0.00555  -0.1111   0.5156   1.0000
   3.000   0.9193   0.01549   0.00570  -0.1105   0.4955   1.0000
   3.250   0.9438   0.01579   0.00586  -0.1098   0.4754   1.0000
   3.500   0.9680   0.01612   0.00607  -0.1091   0.4558   1.0000
   3.750   0.9922   0.01647   0.00631  -0.1085   0.4366   1.0000
   4.000   1.0161   0.01685   0.00658  -0.1078   0.4192   1.0000
   4.250   1.0399   0.01726   0.00691  -0.1072   0.4042   1.0000
   4.500   1.0638   0.01769   0.00726  -0.1065   0.3916   1.0000
   4.750   1.0875   0.01814   0.00763  -0.1059   0.3811   1.0000
   5.000   1.1115   0.01859   0.00807  -0.1054   0.3720   1.0000
   5.250   1.1357   0.01906   0.00853  -0.1048   0.3645   1.0000
   5.500   1.1598   0.01954   0.00901  -0.1043   0.3578   1.0000
   5.750   1.1840   0.02004   0.00951  -0.1038   0.3522   1.0000
   6.000   1.2084   0.02053   0.01010  -0.1034   0.3465   1.0000
   6.250   1.2327   0.02106   0.01066  -0.1029   0.3418   1.0000
   6.500   1.2571   0.02160   0.01127  -0.1025   0.3371   1.0000
   6.750   1.2814   0.02213   0.01193  -0.1021   0.3322   1.0000
   7.000   1.3057   0.02270   0.01262  -0.1016   0.3280   1.0000
   7.250   1.3279   0.02323   0.01326  -0.1009   0.3198   1.0000
   7.500   1.3474   0.02371   0.01380  -0.0997   0.3071   1.0000
   7.750   1.3670   0.02421   0.01436  -0.0986   0.2959   1.0000
   8.000   1.3849   0.02464   0.01500  -0.0972   0.2821   1.0000
   8.250   1.3998   0.02507   0.01554  -0.0954   0.2611   1.0000
   8.500   1.4165   0.02557   0.01618  -0.0938   0.2424   1.0000
   8.750   1.4311   0.02622   0.01689  -0.0920   0.2152   1.0000
   9.000   1.4427   0.02722   0.01779  -0.0899   0.1629   1.0000
   9.250   1.4200   0.03108   0.02056  -0.0844   0.0531   1.0000
   9.500   1.4127   0.03368   0.02296  -0.0805   0.0259   1.0000
   9.750   1.4138   0.03560   0.02500  -0.0777   0.0231   1.0000
  10.000   1.4131   0.03772   0.02730  -0.0751   0.0209   1.0000
  10.250   1.4105   0.04012   0.02991  -0.0728   0.0193   1.0000
  10.500   1.4063   0.04284   0.03292  -0.0709   0.0184   1.0000
  10.750   1.4001   0.04599   0.03633  -0.0696   0.0178   1.0000
  11.000   1.3930   0.04948   0.04004  -0.0688   0.0175   1.0000
  11.250   1.3854   0.05327   0.04408  -0.0684   0.0172   1.0000
  11.500   1.3757   0.05753   0.04858  -0.0685   0.0171   1.0000
  11.750   1.3644   0.06226   0.05353  -0.0690   0.0169   1.0000
  12.000   1.3517   0.06739   0.05888  -0.0699   0.0168   1.0000
  12.250   1.3381   0.07289   0.06459  -0.0712   0.0167   1.0000
  12.500   1.3239   0.07866   0.07055  -0.0726   0.0165   1.0000
  12.750   1.3101   0.08458   0.07665  -0.0743   0.0164   1.0000
  13.000   1.2973   0.09044   0.08268  -0.0760   0.0163   1.0000
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