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GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 269 AIRFOIL (goe269-il)
Reynolds number: 100,000
Max Cl/Cd: 59.14 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe269-il-100000.txt
Download as CSV file: xf-goe269-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 269 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  -0.3467   0.10527   0.10028  -0.0129   1.0000   0.0626
  -8.000  -0.3416   0.10286   0.09792  -0.0147   1.0000   0.0646
  -7.750  -0.3418   0.10211   0.09725  -0.0183   1.0000   0.0661
  -7.500  -0.3340   0.10227   0.09746  -0.0292   1.0000   0.0668
  -7.250  -0.3256   0.09729   0.09253  -0.0296   1.0000   0.0674
  -7.000  -0.3179   0.09175   0.08703  -0.0242   1.0000   0.0685
  -6.750  -0.3089   0.08824   0.08354  -0.0235   1.0000   0.0698
  -6.500  -0.3002   0.08530   0.08065  -0.0242   1.0000   0.0715
  -6.250  -0.2920   0.08262   0.07802  -0.0255   1.0000   0.0733
  -6.000  -0.2840   0.08016   0.07561  -0.0273   1.0000   0.0755
  -5.750  -0.2591   0.08018   0.07552  -0.0404   1.0000   0.0791
  -5.500  -0.2538   0.07654   0.07192  -0.0407   1.0000   0.0799
  -5.250  -0.2574   0.07307   0.06857  -0.0358   1.0000   0.0807
  -5.000  -0.2576   0.07059   0.06616  -0.0330   1.0000   0.0818
  -4.750  -0.2552   0.06851   0.06413  -0.0317   1.0000   0.0833
  -4.500  -0.2499   0.06654   0.06217  -0.0316   1.0000   0.0852
  -4.250  -0.2395   0.06454   0.06015  -0.0330   1.0000   0.0880
  -4.000  -0.1802   0.06058   0.05589  -0.0470   0.9953   0.0939
  -3.750  -0.1517   0.05653   0.05189  -0.0492   0.9887   0.0978
  -3.500  -0.0791   0.05281   0.04773  -0.0634   0.9816   0.1081
  -3.250  -0.0447   0.04871   0.04370  -0.0666   0.9734   0.1121
  -3.000   0.0148   0.04547   0.04012  -0.0761   0.9652   0.1238
  -2.750   0.0656   0.04263   0.03706  -0.0828   0.9583   0.1382
  -2.500   0.1115   0.04015   0.03439  -0.0881   0.9503   0.1526
  -2.250   0.1574   0.03713   0.03128  -0.0932   0.9440   0.1679
  -2.000   0.1992   0.03439   0.02850  -0.0973   0.9369   0.1853
  -1.750   0.2423   0.03212   0.02614  -0.1014   0.9292   0.2147
  -0.500   0.4567   0.02384   0.01598  -0.1129   0.8806   0.1525
  -0.250   0.4864   0.02245   0.01444  -0.1126   0.8674   0.1435
   0.000   0.5172   0.02166   0.01324  -0.1119   0.8543   0.1354
   0.250   0.5457   0.02099   0.01233  -0.1111   0.8410   0.1367
   0.500   0.5723   0.02008   0.01146  -0.1104   0.8276   0.1444
   0.750   0.5996   0.01948   0.01072  -0.1093   0.8143   0.1484
   1.000   0.6260   0.01891   0.01011  -0.1082   0.8005   0.1577
   1.250   0.6523   0.01853   0.00961  -0.1069   0.7864   0.1659
   1.500   0.6778   0.01803   0.00918  -0.1057   0.7718   0.1770
   1.750   0.7033   0.01767   0.00881  -0.1044   0.7565   0.1879
   2.000   0.7292   0.01745   0.00855  -0.1033   0.7404   0.1993
   2.250   0.7554   0.01729   0.00839  -0.1024   0.7237   0.2214
   2.500   0.7820   0.01703   0.00833  -0.1016   0.7068   0.2741
   2.750   0.8043   0.01588   0.00825  -0.0996   0.6906   1.0000
   3.000   0.8305   0.01617   0.00831  -0.0987   0.6736   1.0000
   3.250   0.8566   0.01647   0.00846  -0.0979   0.6570   1.0000
   3.500   0.8828   0.01679   0.00868  -0.0972   0.6408   1.0000
   3.750   0.9088   0.01708   0.00887  -0.0964   0.6243   1.0000
   4.000   0.9345   0.01728   0.00896  -0.0955   0.6065   1.0000
   4.250   0.9600   0.01739   0.00897  -0.0945   0.5881   1.0000
   4.500   0.9853   0.01756   0.00908  -0.0936   0.5693   1.0000
   4.750   1.0111   0.01781   0.00931  -0.0929   0.5530   1.0000
   5.000   1.0369   0.01808   0.00956  -0.0923   0.5377   1.0000
   5.250   1.0627   0.01836   0.00986  -0.0917   0.5225   1.0000
   5.500   1.0882   0.01864   0.01014  -0.0910   0.5066   1.0000
   5.750   1.1134   0.01894   0.01044  -0.0903   0.4902   1.0000
   6.000   1.1385   0.01928   0.01081  -0.0896   0.4735   1.0000
   6.250   1.1633   0.01967   0.01119  -0.0889   0.4564   1.0000
   6.500   1.1878   0.02010   0.01158  -0.0880   0.4380   1.0000
   6.750   1.2114   0.02059   0.01205  -0.0871   0.4175   1.0000
   7.000   1.2342   0.02109   0.01261  -0.0861   0.3939   1.0000
   7.250   1.2560   0.02164   0.01316  -0.0850   0.3680   1.0000
   7.500   1.2768   0.02222   0.01370  -0.0837   0.3393   1.0000
   7.750   1.2968   0.02291   0.01432  -0.0824   0.3103   1.0000
   8.000   1.3166   0.02370   0.01504  -0.0811   0.2842   1.0000
   8.250   1.3364   0.02459   0.01595  -0.0798   0.2606   1.0000
   8.500   1.3556   0.02550   0.01677  -0.0786   0.2411   1.0000
   8.750   1.3735   0.02640   0.01769  -0.0772   0.2212   1.0000
   9.000   1.3895   0.02727   0.01856  -0.0758   0.2010   1.0000
   9.250   1.4043   0.02834   0.01956  -0.0743   0.1829   1.0000
   9.500   1.4187   0.02953   0.02079  -0.0727   0.1664   1.0000
   9.750   1.4311   0.03081   0.02217  -0.0709   0.1493   1.0000
  10.000   1.4399   0.03228   0.02371  -0.0687   0.1306   1.0000
  10.250   1.4424   0.03425   0.02565  -0.0658   0.1094   1.0000
  10.500   1.4410   0.03634   0.02775  -0.0625   0.0892   1.0000
  10.750   1.4393   0.03836   0.02979  -0.0591   0.0773   1.0000
  11.000   1.4410   0.04062   0.03208  -0.0563   0.0697   1.0000
  11.250   1.4445   0.04278   0.03422  -0.0541   0.0644   1.0000
  11.500   1.4519   0.04532   0.03685  -0.0520   0.0601   1.0000
  11.750   1.4572   0.04762   0.03932  -0.0502   0.0565   1.0000
  12.000   1.4634   0.04995   0.04160  -0.0486   0.0532   1.0000
  12.250   1.4716   0.05298   0.04481  -0.0470   0.0509   1.0000
  12.500   1.4752   0.05603   0.04816  -0.0454   0.0495   1.0000
  12.750   1.4760   0.05935   0.05180  -0.0439   0.0483   1.0000
  13.000   1.4736   0.06294   0.05566  -0.0426   0.0474   1.0000
  13.250   1.4678   0.06681   0.05981  -0.0416   0.0468   1.0000
  13.500   1.4584   0.07100   0.06426  -0.0410   0.0462   1.0000
  13.750   1.4460   0.07560   0.06912  -0.0410   0.0458   1.0000
  14.000   1.4310   0.08062   0.07441  -0.0416   0.0455   1.0000
  14.250   1.4122   0.08640   0.08045  -0.0430   0.0454   1.0000
  14.500   1.3862   0.09353   0.08790  -0.0456   0.0458   1.0000
  14.750   1.3489   0.10308   0.09780  -0.0507   0.0468   1.0000
  15.000   1.3107   0.11388   0.10887  -0.0573   0.0480   1.0000
  15.250   1.2728   0.12619   0.12140  -0.0655   0.0492   1.0000
  15.500   1.2353   0.13997   0.13532  -0.0749   0.0505   1.0000
  15.750   1.2048   0.15351   0.14891  -0.0835   0.0516   1.0000
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