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GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 549 AIRFOIL (goe549-il)
Reynolds number: 200,000
Max Cl/Cd: 75.68 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe549-il-200000-n5.txt
Download as CSV file: xf-goe549-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 549 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2728   0.10376   0.10025  -0.0492   1.0000   0.0279
 -10.250  -0.2576   0.10016   0.09665  -0.0515   0.9867   0.0272
 -10.000  -0.2441   0.09600   0.09249  -0.0553   0.9726   0.0265
  -9.750  -0.2315   0.09089   0.08736  -0.0605   0.9582   0.0258
  -9.500  -0.2187   0.08507   0.08152  -0.0669   0.9436   0.0252
  -9.250  -0.2064   0.07850   0.07490  -0.0746   0.9293   0.0248
  -8.750  -0.2899   0.04317   0.03892  -0.1091   0.8769   0.0231
  -8.500  -0.2910   0.03958   0.03501  -0.1098   0.8604   0.0233
  -8.250  -0.2837   0.03714   0.03231  -0.1096   0.8458   0.0236
  -8.000  -0.2741   0.03492   0.02983  -0.1090   0.8319   0.0240
  -7.750  -0.2635   0.03260   0.02719  -0.1082   0.8183   0.0245
  -7.500  -0.2502   0.03058   0.02484  -0.1074   0.8049   0.0253
  -7.250  -0.2356   0.02860   0.02246  -0.1063   0.7907   0.0264
  -7.000  -0.2194   0.02676   0.02013  -0.1051   0.7762   0.0276
  -6.750  -0.2007   0.02540   0.01828  -0.1040   0.7617   0.0284
  -6.500  -0.1814   0.02355   0.01623  -0.1032   0.7477   0.0292
  -6.250  -0.1595   0.02249   0.01498  -0.1025   0.7337   0.0300
  -6.000  -0.1366   0.02165   0.01396  -0.1018   0.7204   0.0310
  -5.750  -0.1131   0.02095   0.01306  -0.1011   0.7081   0.0325
  -5.500  -0.0892   0.02020   0.01205  -0.1005   0.6972   0.0339
  -5.250  -0.0645   0.01961   0.01120  -0.0998   0.6874   0.0350
  -5.000  -0.0401   0.01881   0.01019  -0.0992   0.6791   0.0360
  -4.750  -0.0158   0.01792   0.00922  -0.0987   0.6711   0.0369
  -4.500   0.0089   0.01728   0.00848  -0.0981   0.6644   0.0376
  -4.250   0.0340   0.01675   0.00788  -0.0976   0.6576   0.0383
  -4.000   0.0591   0.01630   0.00733  -0.0971   0.6515   0.0391
  -3.750   0.0844   0.01591   0.00687  -0.0966   0.6459   0.0403
  -3.500   0.1099   0.01558   0.00647  -0.0962   0.6403   0.0417
  -3.250   0.1355   0.01527   0.00606  -0.0957   0.6352   0.0426
  -3.000   0.1611   0.01499   0.00570  -0.0953   0.6301   0.0433
  -2.750   0.1870   0.01476   0.00540  -0.0949   0.6250   0.0440
  -2.500   0.2129   0.01452   0.00508  -0.0945   0.6201   0.0451
  -2.250   0.2390   0.01433   0.00481  -0.0941   0.6156   0.0467
  -2.000   0.2653   0.01416   0.00461  -0.0938   0.6104   0.0489
  -1.750   0.2917   0.01405   0.00442  -0.0935   0.6054   0.0519
  -1.500   0.3182   0.01392   0.00427  -0.0932   0.6010   0.0600
  -1.250   0.3434   0.01361   0.00418  -0.0928   0.5956   0.1094
  -1.000   0.3676   0.01314   0.00409  -0.0924   0.5906   0.2152
  -0.750   0.3924   0.01286   0.00406  -0.0920   0.5862   0.3171
  -0.500   0.4167   0.01258   0.00410  -0.0914   0.5813   0.4078
  -0.250   0.4403   0.01234   0.00418  -0.0906   0.5763   0.5072
   0.000   0.4647   0.01222   0.00422  -0.0898   0.5718   0.5812
   0.250   0.4880   0.01204   0.00428  -0.0887   0.5675   0.6618
   0.500   0.5112   0.01181   0.00435  -0.0875   0.5622   0.7405
   0.750   0.5809   0.01149   0.00438  -0.0956   0.5565   0.9579
   1.000   0.6241   0.01159   0.00438  -0.0990   0.5512   1.0000
   1.250   0.6482   0.01169   0.00442  -0.0983   0.5458   1.0000
   1.500   0.6726   0.01180   0.00444  -0.0976   0.5409   1.0000
   1.750   0.6971   0.01192   0.00449  -0.0970   0.5360   1.0000
   2.000   0.7214   0.01202   0.00456  -0.0963   0.5301   1.0000
   2.250   0.7460   0.01214   0.00461  -0.0957   0.5249   1.0000
   2.500   0.7706   0.01227   0.00469  -0.0951   0.5195   1.0000
   2.750   0.7951   0.01238   0.00479  -0.0944   0.5134   1.0000
   3.000   0.8196   0.01251   0.00485  -0.0938   0.5079   1.0000
   3.250   0.8440   0.01264   0.00498  -0.0932   0.5014   1.0000
   3.500   0.8684   0.01278   0.00508  -0.0925   0.4953   1.0000
   3.750   0.8927   0.01293   0.00521  -0.0919   0.4891   1.0000
   4.000   0.9168   0.01308   0.00534  -0.0912   0.4821   1.0000
   4.250   0.9408   0.01324   0.00546  -0.0905   0.4759   1.0000
   4.500   0.9648   0.01341   0.00565  -0.0899   0.4688   1.0000
   4.750   0.9884   0.01359   0.00578  -0.0891   0.4623   1.0000
   5.000   1.0120   0.01377   0.00599  -0.0884   0.4547   1.0000
   5.250   1.0351   0.01398   0.00616  -0.0876   0.4477   1.0000
   5.500   1.0584   0.01419   0.00640  -0.0868   0.4404   1.0000
   5.750   1.0810   0.01442   0.00661  -0.0860   0.4333   1.0000
   6.000   1.1037   0.01465   0.00686  -0.0852   0.4258   1.0000
   6.250   1.1258   0.01491   0.00711  -0.0842   0.4186   1.0000
   6.500   1.1480   0.01517   0.00739  -0.0834   0.4118   1.0000
   6.750   1.1693   0.01545   0.00767  -0.0823   0.4041   1.0000
   7.000   1.1898   0.01574   0.00797  -0.0811   0.3950   1.0000
   7.250   1.2088   0.01608   0.00827  -0.0797   0.3858   1.0000
   7.500   1.2279   0.01639   0.00862  -0.0784   0.3756   1.0000
   7.750   1.2464   0.01675   0.00897  -0.0769   0.3669   1.0000
   8.000   1.2645   0.01711   0.00934  -0.0754   0.3588   1.0000
   8.250   1.2819   0.01749   0.00976  -0.0739   0.3506   1.0000
   8.500   1.2978   0.01789   0.01017  -0.0720   0.3432   1.0000
   8.750   1.3124   0.01830   0.01061  -0.0700   0.3353   1.0000
   9.000   1.3255   0.01876   0.01108  -0.0677   0.3275   1.0000
   9.250   1.3400   0.01922   0.01160  -0.0658   0.3206   1.0000
   9.500   1.3521   0.01975   0.01215  -0.0635   0.3125   1.0000
   9.750   1.3643   0.02031   0.01276  -0.0615   0.3037   1.0000
  10.000   1.3734   0.02101   0.01345  -0.0590   0.2942   1.0000
  10.250   1.3847   0.02168   0.01418  -0.0571   0.2848   1.0000
  10.500   1.3955   0.02242   0.01498  -0.0551   0.2780   1.0000
  10.750   1.4068   0.02317   0.01582  -0.0534   0.2704   1.0000
  11.000   1.4159   0.02407   0.01677  -0.0515   0.2627   1.0000
  11.250   1.4234   0.02510   0.01784  -0.0496   0.2529   1.0000
  11.500   1.4296   0.02626   0.01905  -0.0477   0.2416   1.0000
  11.750   1.4333   0.02766   0.02047  -0.0458   0.2288   1.0000
  12.000   1.4344   0.02931   0.02214  -0.0439   0.2141   1.0000
  12.250   1.4314   0.03138   0.02418  -0.0420   0.1965   1.0000
  12.500   1.4247   0.03390   0.02664  -0.0403   0.1760   1.0000
  12.750   1.4156   0.03682   0.02949  -0.0387   0.1544   1.0000
  13.000   1.4011   0.04045   0.03301  -0.0374   0.1295   1.0000
  13.250   1.3863   0.04434   0.03681  -0.0365   0.1088   1.0000
  13.500   1.3765   0.04790   0.04034  -0.0359   0.0973   1.0000
  13.750   1.3677   0.05149   0.04394  -0.0355   0.0891   1.0000
  14.000   1.3616   0.05490   0.04741  -0.0352   0.0825   1.0000
  14.250   1.3539   0.05859   0.05115  -0.0352   0.0769   1.0000
  14.500   1.3511   0.06181   0.05447  -0.0352   0.0704   1.0000
  14.750   1.3445   0.06558   0.05830  -0.0354   0.0648   1.0000
  15.000   1.3407   0.06910   0.06192  -0.0356   0.0574   1.0000
  15.250   1.3341   0.07308   0.06595  -0.0361   0.0505   1.0000
  15.500   1.3257   0.07741   0.07031  -0.0368   0.0439   1.0000
  15.750   1.3173   0.08183   0.07477  -0.0376   0.0391   1.0000
  16.000   1.3102   0.08619   0.07918  -0.0385   0.0360   1.0000
  16.250   1.3030   0.09065   0.08371  -0.0395   0.0334   1.0000
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