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GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il)
Reynolds number: 50,000
Max Cl/Cd: 59.18 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe79-il-50000.txt
Download as CSV file: xf-goe79-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 79 (PFALZ 11) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3337   0.11851   0.11134  -0.0099   1.0000   0.0809
  -8.750  -0.3312   0.11749   0.11039  -0.0120   1.0000   0.0824
  -8.500  -0.3324   0.11743   0.11044  -0.0145   1.0000   0.0831
  -8.250  -0.3255   0.11419   0.10729  -0.0158   1.0000   0.0839
  -8.000  -0.3091   0.10762   0.10070  -0.0137   1.0000   0.0870
  -7.750  -0.3023   0.10486   0.09800  -0.0142   1.0000   0.0900
  -7.500  -0.2960   0.10277   0.09599  -0.0159   1.0000   0.0930
  -7.250  -0.2892   0.10210   0.09540  -0.0205   1.0000   0.0952
  -7.000  -0.2788   0.10132   0.09471  -0.0264   1.0000   0.0962
  -6.750  -0.2714   0.09506   0.08851  -0.0214   1.0000   0.0984
  -6.500  -0.2626   0.09197   0.08549  -0.0213   1.0000   0.1015
  -6.250  -0.2534   0.08970   0.08328  -0.0230   1.0000   0.1050
  -6.000  -0.2392   0.08935   0.08298  -0.0295   1.0000   0.1083
  -5.750  -0.2314   0.08605   0.07977  -0.0297   1.0000   0.1098
  -5.500  -0.2279   0.08246   0.07630  -0.0268   1.0000   0.1127
  -5.250  -0.2212   0.08024   0.07415  -0.0268   1.0000   0.1167
  -5.000  -0.1977   0.08102   0.07485  -0.0359   1.0000   0.1224
  -4.750  -0.2036   0.07663   0.07064  -0.0303   1.0000   0.1245
  -4.500  -0.2019   0.07423   0.06832  -0.0282   1.0000   0.1288
  -4.250  -0.1762   0.07438   0.06835  -0.0360   1.0000   0.1372
  -4.000  -0.1808   0.07070   0.06483  -0.0318   1.0000   0.1398
  -3.750  -0.1753   0.06860   0.06279  -0.0309   1.0000   0.1455
  -3.500  -0.1531   0.06736   0.06148  -0.0359   1.0000   0.1541
  -3.250  -0.1492   0.06477   0.05898  -0.0341   1.0000   0.1597
  -3.000  -0.1269   0.06327   0.05741  -0.0382   1.0000   0.1709
  -2.750  -0.1035   0.06219   0.05623  -0.0420   1.0000   0.1854
  -2.500  -0.0980   0.05916   0.05333  -0.0402   1.0000   0.1933
  -2.250  -0.0784   0.05732   0.05147  -0.0424   1.0000   0.2092
  -2.000  -0.0528   0.05586   0.04993  -0.0462   1.0000   0.2338
  -1.750  -0.0201   0.05277   0.04688  -0.0497   0.9939   0.2710
  -1.250   0.0449   0.04590   0.04029  -0.0537   0.9724   0.4505
  -1.000   0.0754   0.04255   0.03707  -0.0535   0.9596   0.5344
  -0.750   0.1126   0.03959   0.03421  -0.0547   0.9458   0.6026
  -0.500   0.1587   0.03706   0.03172  -0.0583   0.9314   0.6539
  -0.250   0.2224   0.03505   0.02964  -0.0666   0.9163   0.6842
   0.000   0.2978   0.03327   0.02773  -0.0777   0.9009   0.6899
   0.250   0.4587   0.03401   0.02720  -0.1093   0.8814   0.4944
   0.500   0.5404   0.03433   0.02666  -0.1187   0.8642   0.3585
   0.750   0.5991   0.03428   0.02597  -0.1222   0.8472   0.2793
   1.000   0.6451   0.03342   0.02483  -0.1236   0.8300   0.2412
   1.250   0.6396   0.01767   0.00947  -0.1132   0.7767   0.2247
   1.500   0.6716   0.01733   0.00888  -0.1124   0.7570   0.2080
   1.750   0.7024   0.01711   0.00836  -0.1112   0.7366   0.1944
   2.000   0.7337   0.01682   0.00775  -0.1098   0.7169   0.1837
   2.250   0.7636   0.01618   0.00696  -0.1081   0.6975   0.1781
   2.500   0.7919   0.01571   0.00633  -0.1063   0.6786   0.1757
   2.750   0.8188   0.01533   0.00583  -0.1045   0.6601   0.1782
   3.000   0.8449   0.01513   0.00550  -0.1027   0.6420   0.1815
   3.250   0.8684   0.01544   0.00573  -0.1012   0.6232   0.1843
   3.500   0.8925   0.01571   0.00599  -0.1000   0.6058   0.1914
   3.750   0.9186   0.01581   0.00606  -0.0988   0.5906   0.2106
   4.000   0.9397   0.01588   0.00735  -0.0978   0.5760   0.9056
   4.250   0.9619   0.01732   0.00859  -0.0967   0.5616   1.0000
   4.500   0.9824   0.01868   0.00977  -0.0956   0.5484   1.0000
   4.750   1.0066   0.01948   0.01033  -0.0945   0.5375   1.0000
   5.000   1.0272   0.02079   0.01155  -0.0935   0.5261   1.0000
   5.250   1.0403   0.02328   0.01412  -0.0928   0.5152   1.0000
   5.500   1.0679   0.02366   0.01436  -0.0919   0.5074   1.0000
   5.750   1.0729   0.02728   0.01816  -0.0911   0.4960   1.0000
   6.000   1.0926   0.02862   0.01949  -0.0900   0.4859   1.0000
   6.250   1.1202   0.02866   0.01948  -0.0887   0.4751   1.0000
   6.500   1.1181   0.03312   0.02415  -0.0875   0.4643   1.0000
   6.750   1.1439   0.03333   0.02434  -0.0861   0.4531   1.0000
   7.000   1.1778   0.03239   0.02333  -0.0848   0.4421   1.0000
   7.250   1.1566   0.03939   0.03065  -0.0832   0.4326   1.0000
   7.500   1.1892   0.03856   0.02983  -0.0817   0.4207   1.0000
   7.750   1.1043   0.05381   0.04535  -0.0801   0.4153   1.0000
   8.000   1.0335   0.06741   0.05901  -0.0807   0.4108   1.0000
   8.250   0.9274   0.08648   0.07813  -0.0843   0.4167   1.0000
   8.500   0.9397   0.08824   0.07991  -0.0826   0.4018   1.0000
   8.750   0.9559   0.08985   0.08159  -0.0810   0.3891   1.0000
   9.000   0.9742   0.09092   0.08271  -0.0791   0.3744   1.0000
   9.250   0.9363   0.09983   0.09168  -0.0803   0.3677   1.0000
   9.500   0.9911   0.09518   0.08710  -0.0756   0.3422   1.0000
   9.750   0.9966   0.09789   0.08986  -0.0741   0.3264   1.0000
  10.000   0.9354   0.11059   0.10259  -0.0773   0.3213   1.0000
  10.250   0.9423   0.11381   0.10585  -0.0763   0.3088   1.0000
  10.500   0.9089   0.12249   0.11457  -0.0785   0.3072   1.0000
  10.750   0.8898   0.12925   0.12138  -0.0802   0.3075   1.0000
  11.000   0.8810   0.13502   0.12720  -0.0814   0.3093   1.0000
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