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GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 758 AIRFOIL (goe758-il)
Reynolds number: 100,000
Max Cl/Cd: 52.73 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe758-il-100000-n5.txt
Download as CSV file: xf-goe758-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 758 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1879   0.11735   0.11287  -0.0440   1.0000   0.0764
 -11.000  -0.1932   0.11482   0.11039  -0.0454   0.9978   0.0789
 -10.750  -0.2038   0.11115   0.10674  -0.0510   0.9894   0.0804
 -10.500  -0.2054   0.10678   0.10238  -0.0557   0.9813   0.0807
 -10.250  -0.1939   0.10152   0.09713  -0.0584   0.9735   0.0811
 -10.000  -0.1649   0.09704   0.09261  -0.0583   0.9653   0.0826
  -9.750  -0.1443   0.09327   0.08880  -0.0601   0.9570   0.0851
  -9.500  -0.1324   0.08909   0.08460  -0.0631   0.9477   0.0872
  -9.250  -0.1239   0.08443   0.07992  -0.0665   0.9377   0.0871
  -8.750  -0.2656   0.07531   0.07062  -0.0753   0.9497   0.0499
  -8.500  -0.2479   0.07140   0.06669  -0.0793   0.9379   0.0494
  -8.250  -0.2376   0.06551   0.06075  -0.0867   0.9229   0.0486
  -8.000  -0.2343   0.05788   0.05294  -0.0956   0.9067   0.0476
  -7.750  -0.2350   0.05142   0.04616  -0.1010   0.8904   0.0470
  -7.500  -0.2324   0.04637   0.04072  -0.1036   0.8750   0.0471
  -7.250  -0.2250   0.04226   0.03617  -0.1047   0.8610   0.0474
  -7.000  -0.2126   0.03881   0.03225  -0.1051   0.8483   0.0476
  -6.750  -0.1983   0.03602   0.02905  -0.1046   0.8347   0.0474
  -6.500  -0.1818   0.03357   0.02617  -0.1040   0.8216   0.0474
  -6.250  -0.1626   0.03143   0.02361  -0.1034   0.8097   0.0474
  -6.000  -0.1406   0.02954   0.02129  -0.1029   0.7992   0.0476
  -5.750  -0.1193   0.02803   0.01943  -0.1021   0.7869   0.0481
  -5.500  -0.0960   0.02674   0.01778  -0.1015   0.7759   0.0491
  -5.250  -0.0708   0.02560   0.01627  -0.1010   0.7668   0.0499
  -5.000  -0.0469   0.02448   0.01496  -0.1004   0.7559   0.0503
  -4.750  -0.0215   0.02344   0.01378  -0.0999   0.7471   0.0507
  -4.500   0.0036   0.02256   0.01279  -0.0994   0.7379   0.0512
  -4.250   0.0288   0.02180   0.01193  -0.0989   0.7296   0.0519
  -4.000   0.0541   0.02113   0.01118  -0.0984   0.7215   0.0526
  -3.750   0.0791   0.02056   0.01053  -0.0978   0.7138   0.0535
  -3.500   0.1042   0.02006   0.00994  -0.0973   0.7065   0.0549
  -3.250   0.1295   0.01965   0.00942  -0.0967   0.6998   0.0570
  -3.000   0.1545   0.01929   0.00896  -0.0961   0.6926   0.0591
  -2.750   0.1802   0.01887   0.00845  -0.0957   0.6869   0.0611
  -2.500   0.2049   0.01860   0.00813  -0.0951   0.6798   0.0635
  -2.250   0.2311   0.01835   0.00775  -0.0947   0.6738   0.0668
  -2.000   0.2570   0.01811   0.00746  -0.0942   0.6679   0.0720
  -1.750   0.2824   0.01786   0.00724  -0.0938   0.6615   0.0851
  -1.500   0.3083   0.01742   0.00696  -0.0934   0.6562   0.1418
  -1.250   0.3307   0.01668   0.00696  -0.0930   0.6500   0.3313
  -1.000   0.3545   0.01626   0.00704  -0.0922   0.6440   0.4760
  -0.500   0.4019   0.01594   0.00717  -0.0900   0.6324   0.6644
  -0.250   0.4272   0.01569   0.00719  -0.0888   0.6266   0.7635
   0.250   0.5369   0.01558   0.00709  -0.0992   0.6131   1.0000
   0.500   0.5617   0.01575   0.00706  -0.0986   0.6078   1.0000
   0.750   0.5846   0.01596   0.00716  -0.0978   0.6018   1.0000
   1.000   0.6081   0.01616   0.00725  -0.0971   0.5956   1.0000
   1.250   0.6339   0.01634   0.00726  -0.0967   0.5905   1.0000
   1.500   0.6565   0.01658   0.00745  -0.0958   0.5842   1.0000
   1.750   0.6806   0.01678   0.00757  -0.0951   0.5781   1.0000
   2.000   0.7070   0.01696   0.00761  -0.0948   0.5733   1.0000
   2.250   0.7286   0.01722   0.00788  -0.0938   0.5663   1.0000
   2.500   0.7533   0.01742   0.00801  -0.0932   0.5604   1.0000
   2.750   0.7782   0.01763   0.00814  -0.0927   0.5549   1.0000
   3.000   0.8006   0.01788   0.00840  -0.0918   0.5479   1.0000
   3.250   0.8260   0.01806   0.00851  -0.0913   0.5424   1.0000
   3.500   0.8485   0.01832   0.00878  -0.0905   0.5357   1.0000
   3.750   0.8721   0.01854   0.00898  -0.0897   0.5292   1.0000
   4.000   0.8972   0.01872   0.00912  -0.0892   0.5237   1.0000
   4.250   0.9185   0.01901   0.00947  -0.0882   0.5160   1.0000
   4.500   0.9435   0.01918   0.00959  -0.0877   0.5103   1.0000
   4.750   0.9649   0.01949   0.00996  -0.0867   0.5030   1.0000
   5.000   0.9884   0.01971   0.01018  -0.0859   0.4965   1.0000
   5.250   1.0111   0.01997   0.01045  -0.0851   0.4899   1.0000
   5.500   1.0330   0.02025   0.01079  -0.0842   0.4827   1.0000
   5.750   1.0571   0.02046   0.01097  -0.0835   0.4768   1.0000
   6.000   1.0770   0.02084   0.01143  -0.0824   0.4690   1.0000
   6.250   1.1011   0.02104   0.01162  -0.0817   0.4631   1.0000
   6.500   1.1203   0.02146   0.01214  -0.0804   0.4554   1.0000
   6.750   1.1430   0.02174   0.01242  -0.0796   0.4491   1.0000
   7.000   1.1632   0.02214   0.01290  -0.0785   0.4424   1.0000
   7.250   1.1837   0.02251   0.01333  -0.0775   0.4356   1.0000
   7.500   1.2055   0.02286   0.01370  -0.0766   0.4296   1.0000
   7.750   1.2234   0.02335   0.01430  -0.0752   0.4224   1.0000
   8.000   1.2462   0.02366   0.01461  -0.0744   0.4168   1.0000
   8.250   1.2616   0.02423   0.01531  -0.0727   0.4093   1.0000
   8.500   1.2814   0.02459   0.01570  -0.0715   0.4025   1.0000
   8.750   1.2971   0.02514   0.01635  -0.0699   0.3955   1.0000
   9.000   1.3140   0.02563   0.01692  -0.0684   0.3889   1.0000
   9.250   1.3329   0.02611   0.01746  -0.0671   0.3833   1.0000
   9.500   1.3438   0.02677   0.01827  -0.0648   0.3765   1.0000
   9.750   1.3621   0.02719   0.01870  -0.0635   0.3705   1.0000
  10.000   1.3685   0.02797   0.01963  -0.0606   0.3633   1.0000
  10.250   1.3811   0.02852   0.02025  -0.0586   0.3562   1.0000
  10.500   1.3861   0.02936   0.02120  -0.0558   0.3480   1.0000
  10.750   1.3960   0.02997   0.02182  -0.0536   0.3392   1.0000
  11.000   1.3950   0.03118   0.02318  -0.0506   0.3301   1.0000
  11.250   1.4003   0.03212   0.02415  -0.0483   0.3209   1.0000
  11.500   1.3997   0.03351   0.02568  -0.0459   0.3115   1.0000
  11.750   1.3980   0.03507   0.02733  -0.0436   0.3012   1.0000
  12.000   1.3968   0.03670   0.02899  -0.0416   0.2904   1.0000
  12.250   1.3919   0.03880   0.03120  -0.0397   0.2793   1.0000
  12.500   1.3849   0.04129   0.03380  -0.0382   0.2676   1.0000
  12.750   1.3771   0.04405   0.03664  -0.0370   0.2552   1.0000
  13.000   1.3688   0.04707   0.03973  -0.0361   0.2424   1.0000
  13.250   1.3588   0.05047   0.04318  -0.0354   0.2283   1.0000
  13.500   1.3481   0.05416   0.04692  -0.0351   0.2133   1.0000
  13.750   1.3361   0.05815   0.05094  -0.0350   0.1966   1.0000
  14.000   1.3221   0.06255   0.05533  -0.0351   0.1781   1.0000
  14.250   1.3070   0.06726   0.06000  -0.0354   0.1578   1.0000
  14.500   1.2880   0.07268   0.06533  -0.0361   0.1359   1.0000
  14.750   1.2699   0.07823   0.07081  -0.0370   0.1181   1.0000
  15.000   1.2500   0.08428   0.07679  -0.0383   0.1039   1.0000
  15.250   1.2327   0.09022   0.08271  -0.0398   0.0938   1.0000
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