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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 200,000
Max Cl/Cd: 82.6 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe155-il-200000.txt
Download as CSV file: xf-goe155-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 155 (SSW D.1) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3115   0.09640   0.09323  -0.0277   1.0000   0.0298
  -7.500  -0.3199   0.09556   0.09247  -0.0282   1.0000   0.0299
  -7.250  -0.3292   0.09475   0.09173  -0.0281   0.9984   0.0300
  -7.000  -0.2919   0.08979   0.08671  -0.0411   0.9918   0.0302
  -6.750  -0.2807   0.08351   0.08045  -0.0401   0.9886   0.0308
  -6.500  -0.2596   0.07915   0.07608  -0.0417   0.9854   0.0317
  -6.250  -0.2304   0.07490   0.07180  -0.0478   0.9812   0.0331
  -6.000  -0.1983   0.07059   0.06743  -0.0553   0.9751   0.0350
  -5.750  -0.1265   0.06600   0.06254  -0.0776   0.9676   0.0389
  -5.500  -0.1174   0.06060   0.05722  -0.0767   0.9615   0.0401
  -5.250  -0.0934   0.05734   0.05395  -0.0787   0.9568   0.0418
  -5.000  -0.0675   0.05432   0.05085  -0.0821   0.9477   0.0445
  -4.750  -0.0129   0.04989   0.04601  -0.0939   0.9396   0.0498
  -4.500  -0.0030   0.04691   0.04311  -0.0922   0.9309   0.0514
  -4.250   0.0157   0.04494   0.04111  -0.0920   0.9215   0.0551
  -4.000   0.0569   0.04156   0.03727  -0.0971   0.9136   0.0618
  -3.750   0.0716   0.03908   0.03485  -0.0961   0.9032   0.0636
  -3.500   0.0930   0.03715   0.03284  -0.0959   0.8950   0.0673
  -3.250   0.1271   0.03446   0.02973  -0.0981   0.8875   0.0750
  -3.000   0.1470   0.03261   0.02791  -0.0977   0.8809   0.0787
  -2.750   0.1776   0.03057   0.02552  -0.0988   0.8738   0.0886
  -2.500   0.2002   0.02888   0.02380  -0.0984   0.8680   0.0928
  -2.250   0.2290   0.02717   0.02185  -0.0990   0.8604   0.1034
  -2.000   0.2561   0.02594   0.02035  -0.0988   0.8550   0.1158
  -1.750   0.2817   0.02459   0.01899  -0.0988   0.8471   0.1234
  -1.500   0.3086   0.02361   0.01777  -0.0986   0.8411   0.1444
  -1.250   0.3193   0.00712   0.00158  -0.0930   0.8174   0.1601
  -1.000   0.3753   0.01816   0.01118  -0.0977   0.8280   0.0768
  -0.750   0.4039   0.01680   0.00951  -0.0970   0.8206   0.0673
  -0.500   0.4316   0.01576   0.00812  -0.0961   0.8126   0.0634
  -0.250   0.4585   0.01508   0.00733  -0.0955   0.8031   0.0635
   0.000   0.4846   0.01451   0.00669  -0.0946   0.7946   0.0659
   0.250   0.5114   0.01395   0.00607  -0.0939   0.7839   0.0656
   0.500   0.5379   0.01347   0.00556  -0.0932   0.7728   0.0659
   0.750   0.5644   0.01307   0.00513  -0.0925   0.7623   0.0670
   1.000   0.5912   0.01276   0.00478  -0.0919   0.7522   0.0694
   1.250   0.6185   0.01255   0.00457  -0.0916   0.7413   0.0731
   1.500   0.6458   0.01229   0.00431  -0.0912   0.7308   0.0831
   1.750   0.6662   0.01055   0.00429  -0.0898   0.7215   0.7715
   2.000   0.7006   0.01030   0.00412  -0.0906   0.7085   1.0000
   2.250   0.7275   0.01036   0.00408  -0.0902   0.6950   1.0000
   2.500   0.7543   0.01042   0.00404  -0.0898   0.6805   1.0000
   2.750   0.7811   0.01048   0.00401  -0.0894   0.6651   1.0000
   3.000   0.8078   0.01056   0.00400  -0.0889   0.6487   1.0000
   3.250   0.8345   0.01065   0.00406  -0.0886   0.6294   1.0000
   3.500   0.8611   0.01076   0.00410  -0.0882   0.6090   1.0000
   3.750   0.8873   0.01092   0.00416  -0.0878   0.5873   1.0000
   4.000   0.9134   0.01112   0.00426  -0.0874   0.5639   1.0000
   4.250   0.9392   0.01137   0.00444  -0.0870   0.5403   1.0000
   4.500   0.9646   0.01170   0.00463  -0.0865   0.5173   1.0000
   4.750   0.9899   0.01205   0.00488  -0.0861   0.4931   1.0000
   5.000   1.0146   0.01246   0.00517  -0.0856   0.4678   1.0000
   5.250   1.0389   0.01292   0.00552  -0.0851   0.4438   1.0000
   5.500   1.0635   0.01334   0.00589  -0.0847   0.4205   1.0000
   5.750   1.0875   0.01380   0.00627  -0.0842   0.3968   1.0000
   6.000   1.1115   0.01422   0.00665  -0.0837   0.3733   1.0000
   6.250   1.1354   0.01463   0.00706  -0.0832   0.3509   1.0000
   6.500   1.1589   0.01506   0.00746  -0.0826   0.3277   1.0000
   6.750   1.1812   0.01556   0.00786  -0.0820   0.2951   1.0000
   7.000   1.2014   0.01630   0.00842  -0.0811   0.2512   1.0000
   7.250   1.2063   0.01891   0.00991  -0.0786   0.0812   1.0000
   7.500   1.2201   0.02062   0.01149  -0.0767   0.0519   1.0000
   7.750   1.2356   0.02197   0.01293  -0.0750   0.0450   1.0000
   8.000   1.2511   0.02313   0.01425  -0.0733   0.0412   1.0000
   8.250   1.2638   0.02443   0.01565  -0.0714   0.0380   1.0000
   8.500   1.2715   0.02606   0.01735  -0.0689   0.0360   1.0000
   8.750   1.2738   0.02810   0.01948  -0.0657   0.0345   1.0000
   9.000   1.2779   0.03012   0.02155  -0.0625   0.0336   1.0000
   9.250   1.2900   0.03145   0.02299  -0.0605   0.0326   1.0000
   9.500   1.3024   0.03287   0.02450  -0.0586   0.0310   1.0000
   9.750   1.3164   0.03454   0.02625  -0.0569   0.0297   1.0000
  10.000   1.3345   0.03641   0.02820  -0.0555   0.0289   1.0000
  10.250   1.3574   0.03854   0.03044  -0.0547   0.0282   1.0000
  10.500   1.3846   0.04118   0.03328  -0.0545   0.0280   1.0000
  10.750   1.4072   0.04384   0.03609  -0.0540   0.0274   1.0000
  11.000   1.4242   0.04677   0.03913  -0.0534   0.0262   1.0000
  11.250   1.4390   0.05006   0.04267  -0.0521   0.0260   1.0000
  11.500   1.4367   0.05319   0.04639  -0.0481   0.0279   1.0000
  11.750   1.4361   0.05890   0.05260  -0.0452   0.0313   1.0000
  12.000   1.3125   0.05135   0.04531  -0.0302   0.0287   1.0000
  12.250   1.2999   0.05640   0.05070  -0.0276   0.0303   1.0000
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