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GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 509 AIRFOIL (goe509-il)
Reynolds number: 200,000
Max Cl/Cd: 68.84 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe509-il-200000-n5.txt
Download as CSV file: xf-goe509-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 509 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2959   0.12057   0.11705  -0.0327   1.0000   0.0266
 -10.500  -0.2959   0.11777   0.11428  -0.0326   1.0000   0.0261
 -10.000  -0.3127   0.10760   0.10417  -0.0351   0.9995   0.0188
  -9.750  -0.2975   0.10374   0.10031  -0.0384   0.9969   0.0186
  -9.500  -0.2861   0.09922   0.09580  -0.0425   0.9937   0.0185
  -9.250  -0.2766   0.09464   0.09122  -0.0466   0.9899   0.0185
  -9.000  -0.2666   0.08966   0.08625  -0.0515   0.9861   0.0185
  -8.750  -0.2635   0.08355   0.08015  -0.0573   0.9803   0.0188
  -8.500  -0.2501   0.07952   0.07613  -0.0623   0.9755   0.0191
  -8.250  -0.2304   0.07832   0.07494  -0.0641   0.9702   0.0205
  -8.000  -0.2257   0.07236   0.06897  -0.0712   0.9628   0.0200
  -7.750  -0.2189   0.06800   0.06460  -0.0749   0.9529   0.0204
  -7.500  -0.2110   0.06294   0.05949  -0.0792   0.9437   0.0208
  -7.250  -0.1994   0.05664   0.05307  -0.0845   0.9352   0.0210
  -7.000  -0.1977   0.05100   0.04731  -0.0860   0.9205   0.0212
  -6.750  -0.2081   0.04511   0.04124  -0.0839   0.8968   0.0216
  -6.500  -0.2401   0.02781   0.02244  -0.0812   0.8786   0.0237
  -6.250  -0.2136   0.02713   0.02169  -0.0813   0.8688   0.0245
  -6.000  -0.1879   0.02513   0.01933  -0.0815   0.8611   0.0257
  -5.750  -0.1633   0.02248   0.01608  -0.0811   0.8526   0.0276
  -5.500  -0.1335   0.02098   0.01422  -0.0817   0.8441   0.0297
  -5.250  -0.0991   0.02023   0.01329  -0.0831   0.8359   0.0315
  -5.000  -0.0686   0.01906   0.01179  -0.0835   0.8267   0.0336
  -4.500  -0.0073   0.01755   0.00988  -0.0845   0.8088   0.0382
  -4.250   0.0223   0.01696   0.00910  -0.0847   0.7986   0.0406
  -4.000   0.0512   0.01648   0.00837  -0.0847   0.7885   0.0432
  -3.750   0.0772   0.01579   0.00758  -0.0842   0.7782   0.0452
  -3.500   0.1042   0.01542   0.00714  -0.0840   0.7681   0.0476
  -3.250   0.1297   0.01509   0.00672  -0.0833   0.7583   0.0504
  -3.000   0.1556   0.01471   0.00623  -0.0827   0.7496   0.0526
  -2.750   0.1808   0.01433   0.00577  -0.0820   0.7403   0.0549
  -2.500   0.2050   0.01399   0.00544  -0.0812   0.7307   0.0584
  -2.250   0.2301   0.01375   0.00513  -0.0804   0.7208   0.0617
  -2.000   0.2536   0.01354   0.00484  -0.0793   0.7093   0.0649
  -1.750   0.2772   0.01329   0.00457  -0.0783   0.6981   0.0694
  -1.500   0.3013   0.01313   0.00435  -0.0774   0.6865   0.0765
  -1.250   0.3248   0.01296   0.00415  -0.0763   0.6740   0.0851
  -1.000   0.3480   0.01279   0.00396  -0.0752   0.6604   0.0985
  -0.750   0.3703   0.01257   0.00380  -0.0739   0.6454   0.1277
  -0.500   0.3906   0.01229   0.00383  -0.0724   0.6285   0.2279
  -0.250   0.4128   0.01231   0.00382  -0.0711   0.6093   0.2714
   0.000   0.4345   0.01234   0.00380  -0.0697   0.5884   0.2975
   0.250   0.4556   0.01240   0.00377  -0.0682   0.5655   0.3201
   0.500   0.4751   0.01246   0.00375  -0.0664   0.5403   0.3403
   0.750   0.4936   0.01254   0.00373  -0.0644   0.5153   0.3613
   1.000   0.5114   0.01261   0.00373  -0.0623   0.4942   0.3873
   1.250   0.5290   0.01261   0.00374  -0.0602   0.4796   0.4264
   1.750   0.7044   0.01259   0.00460  -0.0862   0.4492   0.9803
   2.000   0.7458   0.01286   0.00476  -0.0893   0.4405   0.9908
   2.250   0.7903   0.01312   0.00489  -0.0931   0.4337   0.9984
   2.500   0.8188   0.01328   0.00501  -0.0934   0.4280   1.0000
   2.750   0.8395   0.01347   0.00514  -0.0920   0.4219   1.0000
   3.000   0.8597   0.01371   0.00528  -0.0906   0.4164   1.0000
   3.250   0.8810   0.01386   0.00543  -0.0893   0.4104   1.0000
   3.500   0.9014   0.01406   0.00559  -0.0878   0.4043   1.0000
   3.750   0.9217   0.01430   0.00576  -0.0864   0.3992   1.0000
   4.000   0.9431   0.01445   0.00594  -0.0852   0.3945   1.0000
   4.250   0.9639   0.01463   0.00613  -0.0839   0.3896   1.0000
   4.500   0.9843   0.01486   0.00633  -0.0825   0.3852   1.0000
   4.750   1.0051   0.01506   0.00655  -0.0811   0.3808   1.0000
   5.000   1.0255   0.01523   0.00676  -0.0797   0.3751   1.0000
   5.250   1.0450   0.01545   0.00697  -0.0782   0.3695   1.0000
   5.500   1.0643   0.01565   0.00721  -0.0766   0.3629   1.0000
   5.750   1.0823   0.01585   0.00742  -0.0747   0.3541   1.0000
   6.000   1.1002   0.01605   0.00764  -0.0729   0.3451   1.0000
   6.250   1.1172   0.01628   0.00787  -0.0709   0.3361   1.0000
   6.500   1.1352   0.01649   0.00814  -0.0690   0.3269   1.0000
   6.750   1.1515   0.01675   0.00840  -0.0669   0.3185   1.0000
   7.000   1.1687   0.01699   0.00869  -0.0650   0.3084   1.0000
   7.250   1.1833   0.01728   0.00898  -0.0626   0.2966   1.0000
   7.500   1.1950   0.01759   0.00928  -0.0597   0.2839   1.0000
   7.750   1.2043   0.01797   0.00961  -0.0563   0.2682   1.0000
   8.000   1.2128   0.01843   0.01001  -0.0529   0.2518   1.0000
   8.250   1.2223   0.01893   0.01046  -0.0499   0.2384   1.0000
   8.500   1.2322   0.01947   0.01098  -0.0470   0.2270   1.0000
   8.750   1.2423   0.02005   0.01155  -0.0442   0.2178   1.0000
   9.000   1.2542   0.02060   0.01211  -0.0418   0.2098   1.0000
   9.250   1.2645   0.02123   0.01275  -0.0392   0.2031   1.0000
   9.500   1.2768   0.02181   0.01338  -0.0370   0.1968   1.0000
   9.750   1.2863   0.02254   0.01412  -0.0345   0.1904   1.0000
  10.000   1.2982   0.02319   0.01484  -0.0324   0.1855   1.0000
  10.250   1.3096   0.02388   0.01559  -0.0303   0.1803   1.0000
  10.500   1.3188   0.02472   0.01646  -0.0280   0.1751   1.0000
  10.750   1.3295   0.02551   0.01732  -0.0261   0.1691   1.0000
  11.000   1.3388   0.02640   0.01827  -0.0241   0.1626   1.0000
  11.250   1.3465   0.02744   0.01936  -0.0220   0.1563   1.0000
  11.500   1.3571   0.02834   0.02037  -0.0203   0.1484   1.0000
  11.750   1.3650   0.02946   0.02154  -0.0186   0.1393   1.0000
  12.000   1.3708   0.03078   0.02287  -0.0168   0.1182   1.0000
  12.250   1.3603   0.03340   0.02522  -0.0141   0.0866   1.0000
  12.500   1.3534   0.03594   0.02771  -0.0120   0.0719   1.0000
  13.000   1.3344   0.04195   0.03362  -0.0085   0.0411   1.0000
  13.250   1.3289   0.04482   0.03657  -0.0074   0.0380   1.0000
  13.500   1.3266   0.04751   0.03939  -0.0066   0.0364   1.0000
  13.750   1.3214   0.05063   0.04265  -0.0060   0.0348   1.0000
  14.000   1.3144   0.05408   0.04624  -0.0057   0.0335   1.0000
  14.250   1.3045   0.05806   0.05035  -0.0057   0.0323   1.0000
  14.500   1.2927   0.06250   0.05494  -0.0060   0.0314   1.0000
  14.750   1.2863   0.06639   0.05898  -0.0065   0.0306   1.0000
  15.000   1.2784   0.07065   0.06340  -0.0072   0.0297   1.0000
  15.250   1.2694   0.07518   0.06807  -0.0082   0.0289   1.0000
  15.500   1.2588   0.08003   0.07308  -0.0093   0.0282   1.0000
  15.750   1.2477   0.08503   0.07820  -0.0105   0.0275   1.0000
  16.000   1.2354   0.09027   0.08357  -0.0120   0.0270   1.0000
  16.250   1.2222   0.09568   0.08909  -0.0135   0.0262   1.0000
  16.500   1.2095   0.10104   0.09455  -0.0151   0.0258   1.0000
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