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GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 373 AIRFOIL (goe373-il)
Reynolds number: 100,000
Max Cl/Cd: 58.99 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe373-il-100000.txt
Download as CSV file: xf-goe373-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 373 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2996   0.10262   0.09772  -0.0234   1.0000   0.0427
  -8.000  -0.3067   0.10263   0.09785  -0.0248   1.0000   0.0434
  -7.750  -0.3123   0.10242   0.09776  -0.0273   1.0000   0.0437
  -7.500  -0.3072   0.09806   0.09346  -0.0265   1.0000   0.0442
  -7.250  -0.2972   0.09298   0.08840  -0.0229   1.0000   0.0456
  -7.000  -0.2935   0.09025   0.08571  -0.0223   1.0000   0.0470
  -6.750  -0.2911   0.08792   0.08345  -0.0223   1.0000   0.0484
  -6.500  -0.2890   0.08571   0.08131  -0.0227   1.0000   0.0499
  -6.250  -0.2869   0.08372   0.07939  -0.0236   1.0000   0.0516
  -6.000  -0.2828   0.08246   0.07818  -0.0268   1.0000   0.0532
  -5.750  -0.2704   0.08236   0.07802  -0.0345   1.0000   0.0541
  -5.500  -0.2739   0.07843   0.07420  -0.0313   1.0000   0.0548
  -5.250  -0.2806   0.07523   0.07111  -0.0257   1.0000   0.0561
  -5.000  -0.2812   0.07310   0.06903  -0.0236   1.0000   0.0580
  -4.750  -0.2772   0.07107   0.06702  -0.0236   1.0000   0.0604
  -4.500  -0.2642   0.06912   0.06503  -0.0265   1.0000   0.0641
  -4.250  -0.2263   0.06658   0.06227  -0.0365   0.9984   0.0668
  -4.000  -0.2052   0.06171   0.05748  -0.0374   0.9921   0.0696
  -3.750  -0.1254   0.05954   0.05476  -0.0539   0.9835   0.0796
  -3.500  -0.1089   0.05387   0.04932  -0.0542   0.9756   0.0821
  -3.250  -0.0524   0.05069   0.04583  -0.0636   0.9680   0.0943
  -3.000  -0.0211   0.04711   0.04229  -0.0664   0.9588   0.1012
  -2.750   0.0247   0.04393   0.03893  -0.0725   0.9493   0.1126
  -2.500   0.0759   0.04077   0.03560  -0.0790   0.9415   0.1292
  -2.250   0.1241   0.03832   0.03287  -0.0846   0.9295   0.1542
  -1.000   0.2983   0.02575   0.02051  -0.0936   0.8768   0.4302
  -0.750   0.3344   0.02381   0.01851  -0.0945   0.8657   0.4821
  -0.500   0.3733   0.02217   0.01670  -0.0963   0.8519   0.4976
  -0.250   0.4511   0.02225   0.01536  -0.1048   0.8372   0.2857
   0.000   0.4965   0.02153   0.01378  -0.1048   0.8224   0.1688
   0.250   0.5298   0.02074   0.01255  -0.1039   0.8068   0.1358
   0.500   0.5594   0.01987   0.01142  -0.1029   0.7908   0.1194
   0.750   0.5875   0.01946   0.01071  -0.1017   0.7736   0.1079
   1.000   0.6140   0.01872   0.00993  -0.1007   0.7569   0.1033
   1.250   0.6406   0.01826   0.00935  -0.0997   0.7405   0.0986
   1.500   0.6672   0.01797   0.00895  -0.0987   0.7244   0.0952
   1.750   0.6928   0.01776   0.00867  -0.0976   0.7082   0.0936
   2.000   0.7181   0.01753   0.00837  -0.0964   0.6922   0.0933
   2.250   0.7443   0.01729   0.00806  -0.0957   0.6762   0.0975
   2.500   0.7706   0.01726   0.00795  -0.0949   0.6607   0.1035
   2.750   0.7969   0.01729   0.00785  -0.0941   0.6451   0.1082
   3.000   0.8232   0.01729   0.00779  -0.0933   0.6290   0.1217
   3.250   0.8534   0.01586   0.00783  -0.0935   0.6126   1.0000
   3.500   0.8789   0.01612   0.00788  -0.0925   0.5969   1.0000
   3.750   0.9042   0.01641   0.00797  -0.0916   0.5813   1.0000
   4.000   0.9293   0.01673   0.00813  -0.0908   0.5661   1.0000
   4.250   0.9542   0.01708   0.00836  -0.0900   0.5510   1.0000
   4.500   0.9789   0.01747   0.00869  -0.0892   0.5366   1.0000
   4.750   1.0035   0.01790   0.00910  -0.0885   0.5232   1.0000
   5.000   1.0280   0.01835   0.00954  -0.0878   0.5103   1.0000
   5.250   1.0525   0.01879   0.00998  -0.0871   0.4977   1.0000
   5.500   1.0771   0.01923   0.01043  -0.0864   0.4855   1.0000
   5.750   1.1021   0.01966   0.01084  -0.0858   0.4739   1.0000
   6.000   1.1263   0.02006   0.01128  -0.0850   0.4614   1.0000
   6.250   1.1495   0.02033   0.01155  -0.0840   0.4459   1.0000
   6.500   1.1706   0.02045   0.01177  -0.0826   0.4262   1.0000
   6.750   1.1918   0.02055   0.01189  -0.0812   0.4063   1.0000
   7.000   1.2130   0.02067   0.01195  -0.0798   0.3864   1.0000
   7.250   1.2323   0.02091   0.01226  -0.0783   0.3639   1.0000
   7.500   1.2518   0.02122   0.01255  -0.0768   0.3425   1.0000
   7.750   1.2700   0.02159   0.01300  -0.0752   0.3181   1.0000
   8.000   1.2886   0.02207   0.01346  -0.0737   0.2974   1.0000
   8.250   1.3068   0.02254   0.01406  -0.0723   0.2737   1.0000
   8.500   1.3246   0.02307   0.01463  -0.0707   0.2506   1.0000
   8.750   1.3420   0.02368   0.01532  -0.0692   0.2274   1.0000
   9.000   1.3578   0.02445   0.01608  -0.0676   0.2022   1.0000
   9.250   1.3697   0.02555   0.01704  -0.0656   0.1739   1.0000
   9.500   1.3805   0.02684   0.01827  -0.0635   0.1466   1.0000
   9.750   1.3886   0.02840   0.01972  -0.0611   0.1019   1.0000
  10.000   1.3859   0.03077   0.02169  -0.0578   0.0658   1.0000
  10.250   1.3821   0.03287   0.02378  -0.0540   0.0556   1.0000
  10.500   1.3785   0.03495   0.02593  -0.0506   0.0508   1.0000
  10.750   1.3768   0.03698   0.02811  -0.0479   0.0475   1.0000
  11.000   1.3723   0.03938   0.03061  -0.0456   0.0447   1.0000
  11.250   1.3636   0.04235   0.03364  -0.0437   0.0428   1.0000
  11.500   1.3622   0.04490   0.03639  -0.0424   0.0413   1.0000
  11.750   1.3597   0.04774   0.03939  -0.0413   0.0401   1.0000
  12.000   1.3572   0.05074   0.04254  -0.0405   0.0391   1.0000
  12.250   1.3561   0.05373   0.04566  -0.0398   0.0384   1.0000
  12.500   1.3567   0.05666   0.04870  -0.0391   0.0377   1.0000
  12.750   1.3595   0.05946   0.05160  -0.0383   0.0370   1.0000
  13.000   1.3649   0.06212   0.05439  -0.0373   0.0364   1.0000
  13.250   1.3728   0.06473   0.05711  -0.0362   0.0359   1.0000
  13.500   1.3815   0.06750   0.06004  -0.0352   0.0356   1.0000
  13.750   1.3882   0.07073   0.06347  -0.0344   0.0355   1.0000
  14.000   1.3895   0.07460   0.06758  -0.0342   0.0355   1.0000
  14.250   1.3857   0.07899   0.07224  -0.0346   0.0355   1.0000
  14.500   1.3786   0.08378   0.07726  -0.0355   0.0353   1.0000
  14.750   1.3661   0.08930   0.08306  -0.0372   0.0354   1.0000
  15.000   1.3497   0.09554   0.08958  -0.0399   0.0356   1.0000
  15.250   1.3303   0.10253   0.09684  -0.0434   0.0358   1.0000
  15.500   1.3053   0.11106   0.10568  -0.0483   0.0365   1.0000
  15.750   1.2723   0.12192   0.11686  -0.0556   0.0374   1.0000
  16.000   1.2359   0.13473   0.12992  -0.0646   0.0384   1.0000
  16.250   1.1961   0.15008   0.14544  -0.0755   0.0394   1.0000
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