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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 100,000
Max Cl/Cd: 55.28 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe325-il-100000-n5.txt
Download as CSV file: xf-goe325-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 325 (PFALZ 54) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3299   0.10460   0.09988  -0.0275   1.0000   0.0414
  -8.000  -0.3344   0.10272   0.09810  -0.0281   1.0000   0.0416
  -7.750  -0.3369   0.10047   0.09592  -0.0292   1.0000   0.0417
  -7.500  -0.3367   0.09787   0.09338  -0.0307   1.0000   0.0418
  -7.250  -0.3351   0.09507   0.09062  -0.0321   1.0000   0.0418
  -7.000  -0.3323   0.09209   0.08768  -0.0335   1.0000   0.0419
  -6.750  -0.3281   0.08896   0.08456  -0.0349   1.0000   0.0419
  -6.500  -0.3237   0.08536   0.08102  -0.0359   1.0000   0.0420
  -6.250  -0.3267   0.08087   0.07661  -0.0304   1.0000   0.0432
  -6.000  -0.3244   0.07841   0.07420  -0.0270   1.0000   0.0451
  -5.750  -0.3197   0.07594   0.07177  -0.0268   1.0000   0.0477
  -5.500  -0.2728   0.07141   0.06697  -0.0430   0.9946   0.0545
  -5.250  -0.2322   0.06610   0.06139  -0.0521   0.9882   0.0549
  -5.000  -0.2064   0.06013   0.05540  -0.0560   0.9830   0.0555
  -4.750  -0.1888   0.05696   0.05233  -0.0556   0.9780   0.0592
  -4.500  -0.1288   0.05338   0.04803  -0.0674   0.9704   0.0681
  -4.250  -0.1060   0.04638   0.04120  -0.0690   0.9659   0.0504
  -4.000  -0.0665   0.04204   0.03653  -0.0740   0.9587   0.0512
  -3.750  -0.0236   0.03778   0.03188  -0.0790   0.9532   0.0509
  -3.500   0.0154   0.03406   0.02774  -0.0824   0.9447   0.0499
  -3.250   0.0606   0.03079   0.02390  -0.0863   0.9373   0.0529
  -3.000   0.0959   0.02814   0.02082  -0.0879   0.9248   0.0527
  -2.750   0.1300   0.02591   0.01818  -0.0890   0.9113   0.0527
  -2.500   0.1626   0.02406   0.01593  -0.0897   0.8968   0.0531
  -2.250   0.1946   0.02268   0.01413  -0.0901   0.8816   0.0555
  -1.750   0.2556   0.02011   0.01111  -0.0905   0.8447   0.0568
  -1.500   0.2874   0.01904   0.00982  -0.0907   0.8234   0.0573
  -1.250   0.3181   0.01813   0.00874  -0.0906   0.7980   0.0581
  -1.000   0.3486   0.01737   0.00778  -0.0905   0.7699   0.0594
  -0.750   0.3777   0.01677   0.00699  -0.0901   0.7401   0.0611
  -0.500   0.4055   0.01631   0.00635  -0.0896   0.7101   0.0634
  -0.250   0.4324   0.01604   0.00586  -0.0890   0.6803   0.0671
   0.000   0.4588   0.01581   0.00552  -0.0885   0.6514   0.0735
   0.250   0.4851   0.01568   0.00520  -0.0879   0.6250   0.0796
   0.500   0.5115   0.01556   0.00488  -0.0873   0.6016   0.0872
   0.750   0.5385   0.01545   0.00464  -0.0870   0.5810   0.1076
   1.000   0.5620   0.01333   0.00455  -0.0859   0.5638   1.0000
   1.250   0.5886   0.01360   0.00449  -0.0855   0.5476   1.0000
   1.500   0.6152   0.01387   0.00451  -0.0852   0.5325   1.0000
   1.750   0.6417   0.01415   0.00458  -0.0848   0.5185   1.0000
   2.000   0.6683   0.01444   0.00470  -0.0845   0.5053   1.0000
   2.250   0.6947   0.01473   0.00484  -0.0843   0.4926   1.0000
   2.500   0.7211   0.01502   0.00499  -0.0840   0.4803   1.0000
   2.750   0.7475   0.01530   0.00518  -0.0837   0.4682   1.0000
   3.000   0.7739   0.01557   0.00539  -0.0835   0.4563   1.0000
   3.250   0.8002   0.01586   0.00561  -0.0832   0.4453   1.0000
   3.500   0.8264   0.01616   0.00585  -0.0829   0.4351   1.0000
   3.750   0.8525   0.01646   0.00611  -0.0826   0.4249   1.0000
   4.000   0.8787   0.01676   0.00639  -0.0824   0.4150   1.0000
   4.250   0.9046   0.01709   0.00667  -0.0821   0.4069   1.0000
   4.500   0.9307   0.01742   0.00704  -0.0819   0.3985   1.0000
   4.750   0.9566   0.01778   0.00738  -0.0816   0.3913   1.0000
   5.000   0.9825   0.01814   0.00777  -0.0813   0.3836   1.0000
   5.250   1.0081   0.01853   0.00817  -0.0810   0.3771   1.0000
   5.500   1.0339   0.01892   0.00864  -0.0808   0.3703   1.0000
   5.750   1.0596   0.01935   0.00907  -0.0805   0.3652   1.0000
   6.000   1.0853   0.01980   0.00966  -0.0803   0.3593   1.0000
   6.250   1.1108   0.02025   0.01019  -0.0800   0.3538   1.0000
   6.500   1.1362   0.02073   0.01071  -0.0797   0.3490   1.0000
   6.750   1.1614   0.02122   0.01138  -0.0794   0.3435   1.0000
   7.000   1.1867   0.02172   0.01203  -0.0791   0.3387   1.0000
   7.250   1.2104   0.02215   0.01258  -0.0785   0.3302   1.0000
   7.500   1.2329   0.02249   0.01298  -0.0777   0.3191   1.0000
   7.750   1.2540   0.02279   0.01337  -0.0768   0.3048   1.0000
   8.000   1.2740   0.02307   0.01381  -0.0757   0.2876   1.0000
   8.250   1.2947   0.02342   0.01437  -0.0746   0.2716   1.0000
   8.500   1.3139   0.02379   0.01488  -0.0734   0.2496   1.0000
   8.750   1.3311   0.02437   0.01547  -0.0720   0.2085   1.0000
   9.000   1.3251   0.02738   0.01739  -0.0686   0.0762   1.0000
   9.500   1.3327   0.03172   0.02153  -0.0632   0.0296   1.0000
   9.750   1.3384   0.03341   0.02336  -0.0607   0.0264   1.0000
  10.000   1.3384   0.03523   0.02534  -0.0577   0.0247   1.0000
  10.250   1.3372   0.03725   0.02758  -0.0549   0.0237   1.0000
  10.500   1.3351   0.03945   0.03001  -0.0525   0.0228   1.0000
  10.750   1.3306   0.04202   0.03280  -0.0505   0.0218   1.0000
  11.000   1.3241   0.04504   0.03603  -0.0491   0.0211   1.0000
  11.250   1.3157   0.04861   0.03981  -0.0486   0.0204   1.0000
  11.500   1.3060   0.05277   0.04418  -0.0489   0.0199   1.0000
  11.750   1.2953   0.05749   0.04909  -0.0499   0.0195   1.0000
  12.000   1.2842   0.06262   0.05440  -0.0513   0.0192   1.0000
  12.250   1.2733   0.06786   0.05981  -0.0529   0.0189   1.0000
  12.500   1.2632   0.07296   0.06506  -0.0543   0.0187   1.0000
  12.750   1.2543   0.07775   0.06998  -0.0555   0.0185   1.0000
  13.000   1.2474   0.08204   0.07437  -0.0561   0.0182   1.0000
  13.250   1.2437   0.08565   0.07807  -0.0563   0.0179   1.0000
  13.500   1.2443   0.08827   0.08075  -0.0555   0.0175   1.0000
  13.750   1.2515   0.08941   0.08191  -0.0531   0.0169   1.0000
  14.000   1.2591   0.09094   0.08348  -0.0510   0.0165   1.0000
  14.250   1.2607   0.09419   0.08691  -0.0511   0.0161   1.0000
  14.500   1.2608   0.09777   0.09068  -0.0516   0.0157   1.0000
  14.750   1.2596   0.10165   0.09480  -0.0524   0.0153   1.0000
  15.000   1.2575   0.10577   0.09911  -0.0534   0.0150   1.0000
  15.250   1.2547   0.11013   0.10367  -0.0546   0.0148   1.0000
  15.500   1.2504   0.11488   0.10862  -0.0561   0.0146   1.0000
  15.750   1.2445   0.12008   0.11402  -0.0582   0.0146   1.0000
  16.000   1.2371   0.12576   0.11990  -0.0608   0.0145   1.0000
  16.250   1.2284   0.13193   0.12627  -0.0640   0.0145   1.0000
  16.500   1.2186   0.13860   0.13315  -0.0678   0.0145   1.0000
  16.750   1.2078   0.14580   0.14054  -0.0721   0.0146   1.0000
  17.000   1.1958   0.15364   0.14856  -0.0770   0.0146   1.0000
  17.250   1.1832   0.16208   0.15717  -0.0824   0.0147   1.0000
  17.500   1.1696   0.17133   0.16657  -0.0885   0.0149   1.0000
  17.750   1.1554   0.18153   0.17690  -0.0952   0.0151   1.0000
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