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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 500,000
Max Cl/Cd: 107.72 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe155-il-500000.txt
Download as CSV file: xf-goe155-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3997   0.12840   0.12621  -0.0038   1.0000   0.0142
 -10.250  -0.3949   0.12543   0.12326  -0.0066   1.0000   0.0142
 -10.000  -0.3899   0.12230   0.12015  -0.0092   1.0000   0.0142
  -9.750  -0.3799   0.11729   0.11515  -0.0088   1.0000   0.0144
  -9.500  -0.3712   0.11376   0.11162  -0.0093   1.0000   0.0146
  -9.250  -0.3629   0.11060   0.10848  -0.0105   1.0000   0.0147
  -9.000  -0.3545   0.10751   0.10541  -0.0121   1.0000   0.0150
  -8.750  -0.3459   0.10442   0.10232  -0.0139   1.0000   0.0153
  -8.500  -0.3369   0.10129   0.09921  -0.0160   1.0000   0.0157
  -8.250  -0.3277   0.09810   0.09604  -0.0183   1.0000   0.0162
  -8.000  -0.3181   0.09486   0.09282  -0.0209   1.0000   0.0169
  -7.750  -0.3022   0.09113   0.08910  -0.0267   0.9789   0.0179
  -7.500  -0.2926   0.08805   0.08599  -0.0323   0.9574   0.0181
  -7.250  -0.2825   0.08477   0.08267  -0.0368   0.9414   0.0182
  -7.000  -0.2690   0.08111   0.07897  -0.0409   0.9286   0.0182
  -6.750  -0.2518   0.07722   0.07503  -0.0454   0.9170   0.0183
  -6.500  -0.2494   0.07327   0.07108  -0.0428   0.9082   0.0187
  -6.250  -0.2369   0.07052   0.06827  -0.0435   0.8990   0.0190
  -6.000  -0.2192   0.06740   0.06512  -0.0462   0.8885   0.0195
  -5.750  -0.1992   0.06414   0.06178  -0.0497   0.8789   0.0201
  -5.500  -0.1765   0.06065   0.05820  -0.0537   0.8700   0.0212
  -5.250  -0.1308   0.05570   0.05308  -0.0643   0.8605   0.0232
  -5.000  -0.0988   0.05145   0.04865  -0.0693   0.8529   0.0234
  -4.750  -0.0762   0.04561   0.04270  -0.0732   0.8447   0.0239
  -4.500  -0.0561   0.04331   0.04032  -0.0740   0.8369   0.0244
  -4.250  -0.0317   0.04096   0.03787  -0.0755   0.8286   0.0252
  -4.000  -0.0034   0.03826   0.03503  -0.0777   0.8213   0.0266
  -3.750   0.0382   0.03505   0.03150  -0.0808   0.8146   0.0299
  -3.500   0.0678   0.02936   0.02547  -0.0835   0.8092   0.0310
  -3.250   0.0927   0.02776   0.02382  -0.0843   0.8025   0.0319
  -3.000   0.1193   0.02622   0.02213  -0.0850   0.7968   0.0333
  -2.750   0.1491   0.02421   0.01992  -0.0857   0.7908   0.0360
  -2.500   0.1814   0.02080   0.01603  -0.0866   0.7849   0.0405
  -2.250   0.2077   0.02004   0.01524  -0.0869   0.7787   0.0424
  -2.000   0.2388   0.01884   0.01359  -0.0871   0.7717   0.0503
  -1.750   0.2650   0.01746   0.01221  -0.0875   0.7648   0.0527
  -1.500   0.2947   0.01840   0.01296  -0.0871   0.7567   0.0607
  -1.250   0.3216   0.01577   0.01021  -0.0879   0.7500   0.0650
  -1.000   0.3511   0.01669   0.01096  -0.0875   0.7416   0.0733
  -0.750   0.3783   0.01435   0.00856  -0.0882   0.7344   0.0792
  -0.500   0.4115   0.01165   0.00522  -0.0873   0.7270   0.0460
  -0.250   0.4403   0.01061   0.00397  -0.0870   0.7191   0.0415
   0.000   0.4687   0.01017   0.00345  -0.0869   0.7101   0.0410
   0.250   0.4970   0.00982   0.00307  -0.0869   0.7018   0.0408
   0.500   0.5251   0.00955   0.00275  -0.0869   0.6933   0.0410
   0.750   0.5535   0.00929   0.00250  -0.0869   0.6835   0.0423
   1.000   0.5818   0.00912   0.00230  -0.0869   0.6737   0.0426
   1.250   0.6100   0.00900   0.00214  -0.0869   0.6633   0.0428
   1.500   0.6384   0.00890   0.00203  -0.0870   0.6513   0.0436
   1.750   0.6667   0.00885   0.00195  -0.0870   0.6380   0.0456
   2.000   0.6948   0.00883   0.00189  -0.0870   0.6228   0.0489
   2.250   0.7228   0.00883   0.00190  -0.0870   0.6050   0.0730
   2.500   0.7506   0.00876   0.00197  -0.0871   0.5836   0.1618
   2.750   0.7753   0.00723   0.00213  -0.0868   0.5604   1.0000
   3.000   0.8025   0.00745   0.00220  -0.0867   0.5334   1.0000
   3.250   0.8294   0.00771   0.00232  -0.0867   0.5071   1.0000
   3.500   0.8563   0.00798   0.00245  -0.0866   0.4840   1.0000
   3.750   0.8832   0.00824   0.00261  -0.0865   0.4633   1.0000
   4.000   0.9097   0.00854   0.00279  -0.0864   0.4412   1.0000
   4.250   0.9364   0.00881   0.00299  -0.0864   0.4217   1.0000
   4.500   0.9630   0.00909   0.00319  -0.0863   0.4035   1.0000
   4.750   0.9894   0.00938   0.00340  -0.0862   0.3838   1.0000
   5.000   1.0159   0.00965   0.00362  -0.0861   0.3627   1.0000
   5.250   1.0416   0.01001   0.00386  -0.0859   0.3343   1.0000
   5.500   1.0668   0.01043   0.00413  -0.0857   0.3025   1.0000
   5.750   1.0918   0.01088   0.00444  -0.0855   0.2755   1.0000
   6.000   1.1166   0.01134   0.00480  -0.0852   0.2534   1.0000
   6.250   1.1410   0.01182   0.00517  -0.0849   0.2290   1.0000
   6.500   1.1641   0.01247   0.00562  -0.0845   0.1886   1.0000
   6.750   1.1744   0.01489   0.00714  -0.0826   0.0403   1.0000
   7.000   1.1967   0.01561   0.00790  -0.0819   0.0320   1.0000
   7.250   1.2187   0.01633   0.00869  -0.0811   0.0279   1.0000
   7.500   1.2372   0.01746   0.00994  -0.0798   0.0245   1.0000
   7.750   1.2589   0.01809   0.01064  -0.0790   0.0231   1.0000
   8.000   1.2793   0.01882   0.01145  -0.0780   0.0213   1.0000
   8.250   1.2982   0.01964   0.01231  -0.0770   0.0196   1.0000
   8.500   1.3090   0.02121   0.01400  -0.0748   0.0182   1.0000
   8.750   1.3199   0.02263   0.01552  -0.0725   0.0175   1.0000
   9.000   1.3353   0.02355   0.01653  -0.0709   0.0169   1.0000
   9.250   1.3472   0.02466   0.01773  -0.0688   0.0163   1.0000
   9.500   1.3556   0.02583   0.01898  -0.0663   0.0157   1.0000
   9.750   1.3649   0.02698   0.02020  -0.0640   0.0150   1.0000
  10.000   1.3747   0.02813   0.02142  -0.0621   0.0143   1.0000
  10.250   1.3823   0.02954   0.02287  -0.0602   0.0137   1.0000
  10.500   1.3848   0.03171   0.02510  -0.0577   0.0132   1.0000
  10.750   1.3905   0.03459   0.02806  -0.0551   0.0127   1.0000
  11.000   1.4004   0.03598   0.02959  -0.0536   0.0125   1.0000
  11.250   1.4102   0.03766   0.03140  -0.0520   0.0122   1.0000
  11.500   1.4198   0.03956   0.03345  -0.0503   0.0120   1.0000
  11.750   1.4288   0.04171   0.03577  -0.0486   0.0117   1.0000
  12.000   1.4364   0.04415   0.03839  -0.0469   0.0115   1.0000
  12.250   1.4417   0.04687   0.04131  -0.0452   0.0113   1.0000
  12.500   1.4437   0.04957   0.04420  -0.0436   0.0110   1.0000
  12.750   1.4431   0.05243   0.04725  -0.0421   0.0108   1.0000
  13.000   1.4407   0.05523   0.05020  -0.0410   0.0105   1.0000
  13.250   1.4375   0.05813   0.05324  -0.0402   0.0103   1.0000
  13.500   1.4316   0.06157   0.05685  -0.0395   0.0102   1.0000
  13.750   1.4201   0.06615   0.06167  -0.0388   0.0102   1.0000
  14.000   1.3981   0.07249   0.06835  -0.0385   0.0104   1.0000
  14.250   1.3754   0.07899   0.07513  -0.0392   0.0107   1.0000
  14.500   1.3535   0.08549   0.08186  -0.0405   0.0109   1.0000
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