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GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il)
Reynolds number: 100,000
Max Cl/Cd: 56.33 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe326-il-100000.txt
Download as CSV file: xf-goe326-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 326 (PFALZ 55) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3413   0.10484   0.10001  -0.0210   1.0000   0.0610
  -8.250  -0.3442   0.10368   0.09894  -0.0248   1.0000   0.0621
  -8.000  -0.3471   0.10253   0.09789  -0.0301   1.0000   0.0626
  -7.750  -0.3429   0.10063   0.09603  -0.0368   1.0000   0.0629
  -7.500  -0.3352   0.09356   0.08903  -0.0302   1.0000   0.0641
  -7.250  -0.3258   0.08964   0.08514  -0.0270   1.0000   0.0661
  -7.000  -0.3210   0.08687   0.08243  -0.0267   1.0000   0.0685
  -6.750  -0.3199   0.08449   0.08013  -0.0272   1.0000   0.0710
  -6.500  -0.3219   0.08251   0.07821  -0.0281   1.0000   0.0735
  -6.250  -0.3262   0.08158   0.07732  -0.0315   1.0000   0.0758
  -6.000  -0.3241   0.08149   0.07707  -0.0380   1.0000   0.0768
  -5.750  -0.3288   0.07661   0.07235  -0.0337   1.0000   0.0778
  -5.500  -0.3316   0.07366   0.06949  -0.0294   1.0000   0.0790
  -5.250  -0.3309   0.07133   0.06721  -0.0271   1.0000   0.0810
  -5.000  -0.3260   0.06900   0.06488  -0.0267   1.0000   0.0839
  -4.750  -0.2892   0.06677   0.06219  -0.0387   0.9990   0.0919
  -4.500  -0.2732   0.06138   0.05702  -0.0377   0.9946   0.0949
  -4.250  -0.2238   0.05721   0.05255  -0.0475   0.9875   0.1080
  -4.000  -0.1932   0.05357   0.04893  -0.0500   0.9819   0.1152
  -3.750  -0.1517   0.04976   0.04494  -0.0562   0.9744   0.1275
  -3.500  -0.1100   0.04650   0.04153  -0.0616   0.9678   0.1445
  -3.250  -0.0674   0.04351   0.03829  -0.0672   0.9600   0.1699
  -3.000  -0.0267   0.04102   0.03562  -0.0716   0.9524   0.1987
  -2.750   0.0110   0.03823   0.03282  -0.0749   0.9451   0.2300
  -2.000   0.1081   0.03137   0.02621  -0.0782   0.9212   0.4123
  -1.750   0.2231   0.02706   0.01932  -0.0931   0.9159   0.1360
  -1.500   0.2642   0.02477   0.01677  -0.0951   0.9067   0.1266
  -1.250   0.3093   0.02311   0.01470  -0.0970   0.8987   0.1162
  -1.000   0.3437   0.02190   0.01320  -0.0972   0.8862   0.1116
  -0.750   0.3765   0.02094   0.01203  -0.0971   0.8733   0.1100
  -0.500   0.4069   0.02013   0.01117  -0.0967   0.8599   0.1132
  -0.250   0.4357   0.01947   0.01045  -0.0959   0.8458   0.1179
   0.000   0.4633   0.01884   0.00976  -0.0948   0.8313   0.1204
   0.250   0.4894   0.01814   0.00911  -0.0936   0.8164   0.1249
   0.500   0.5151   0.01766   0.00861  -0.0922   0.8012   0.1331
   0.750   0.5416   0.01725   0.00819  -0.0911   0.7860   0.1525
   1.000   0.5722   0.01480   0.00778  -0.0907   0.7714   1.0000
   1.250   0.5985   0.01488   0.00743  -0.0894   0.7557   1.0000
   1.500   0.6243   0.01499   0.00729  -0.0883   0.7399   1.0000
   1.750   0.6501   0.01513   0.00725  -0.0873   0.7241   1.0000
   2.000   0.6758   0.01530   0.00727  -0.0864   0.7084   1.0000
   2.250   0.7016   0.01549   0.00731  -0.0856   0.6928   1.0000
   2.500   0.7274   0.01569   0.00740  -0.0848   0.6774   1.0000
   2.750   0.7532   0.01589   0.00750  -0.0841   0.6622   1.0000
   3.000   0.7791   0.01609   0.00763  -0.0835   0.6473   1.0000
   3.250   0.8050   0.01629   0.00776  -0.0828   0.6326   1.0000
   3.500   0.8309   0.01651   0.00791  -0.0822   0.6181   1.0000
   3.750   0.8568   0.01673   0.00809  -0.0816   0.6038   1.0000
   4.000   0.8827   0.01698   0.00828  -0.0810   0.5895   1.0000
   4.250   0.9085   0.01724   0.00847  -0.0803   0.5747   1.0000
   4.500   0.9341   0.01752   0.00868  -0.0797   0.5597   1.0000
   4.750   0.9595   0.01787   0.00900  -0.0791   0.5450   1.0000
   5.000   0.9849   0.01829   0.00940  -0.0785   0.5311   1.0000
   5.250   1.0102   0.01874   0.00983  -0.0780   0.5174   1.0000
   5.500   1.0351   0.01918   0.01026  -0.0774   0.5033   1.0000
   5.750   1.0601   0.01964   0.01076  -0.0768   0.4903   1.0000
   6.000   1.0852   0.02010   0.01123  -0.0762   0.4778   1.0000
   6.250   1.1099   0.02049   0.01164  -0.0756   0.4645   1.0000
   6.500   1.1346   0.02087   0.01206  -0.0749   0.4514   1.0000
   6.750   1.1582   0.02125   0.01256  -0.0742   0.4378   1.0000
   7.000   1.1817   0.02162   0.01305  -0.0734   0.4241   1.0000
   7.250   1.2049   0.02197   0.01351  -0.0726   0.4100   1.0000
   7.500   1.2276   0.02220   0.01382  -0.0715   0.3937   1.0000
   7.750   1.2480   0.02238   0.01410  -0.0702   0.3733   1.0000
   8.000   1.2670   0.02250   0.01423  -0.0686   0.3493   1.0000
   8.250   1.2843   0.02280   0.01462  -0.0669   0.3226   1.0000
   8.500   1.3011   0.02330   0.01516  -0.0653   0.2952   1.0000
   8.750   1.3168   0.02399   0.01589  -0.0635   0.2668   1.0000
   9.000   1.3307   0.02479   0.01665  -0.0617   0.2374   1.0000
   9.250   1.3444   0.02571   0.01755  -0.0599   0.2120   1.0000
   9.500   1.3576   0.02673   0.01856  -0.0581   0.1919   1.0000
   9.750   1.3692   0.02782   0.01965  -0.0562   0.1690   1.0000
  10.000   1.3765   0.02919   0.02099  -0.0540   0.1463   1.0000
  10.250   1.3770   0.03101   0.02270  -0.0511   0.1245   1.0000
  10.500   1.3726   0.03315   0.02484  -0.0477   0.1008   1.0000
  10.750   1.3659   0.03569   0.02734  -0.0446   0.0786   1.0000
  11.000   1.3607   0.03830   0.02993  -0.0422   0.0663   1.0000
  11.250   1.3546   0.04114   0.03272  -0.0403   0.0603   1.0000
  11.500   1.3525   0.04383   0.03554  -0.0387   0.0558   1.0000
  11.750   1.3500   0.04666   0.03844  -0.0375   0.0526   1.0000
  12.000   1.3453   0.04979   0.04156  -0.0363   0.0502   1.0000
  12.250   1.3466   0.05248   0.04438  -0.0351   0.0478   1.0000
  12.500   1.3483   0.05517   0.04721  -0.0342   0.0454   1.0000
  12.750   1.3492   0.05797   0.05011  -0.0334   0.0433   1.0000
  13.000   1.3516   0.06067   0.05283  -0.0324   0.0417   1.0000
  13.250   1.3613   0.06298   0.05512  -0.0302   0.0404   1.0000
  13.500   1.3672   0.06580   0.05818  -0.0291   0.0398   1.0000
  13.750   1.3709   0.06902   0.06164  -0.0281   0.0392   1.0000
  14.000   1.3704   0.07275   0.06564  -0.0275   0.0389   1.0000
  14.250   1.3655   0.07700   0.07017  -0.0274   0.0387   1.0000
  14.500   1.3564   0.08180   0.07523  -0.0279   0.0386   1.0000
  14.750   1.3432   0.08712   0.08083  -0.0291   0.0386   1.0000
  15.000   1.3272   0.09299   0.08696  -0.0309   0.0386   1.0000
  15.250   1.3090   0.09943   0.09365  -0.0335   0.0387   1.0000
  15.500   1.2892   0.10649   0.10095  -0.0369   0.0390   1.0000
  15.750   1.2680   0.11421   0.10888  -0.0410   0.0392   1.0000
  16.000   1.2459   0.12260   0.11747  -0.0459   0.0396   1.0000
  16.250   1.2235   0.13161   0.12664  -0.0514   0.0399   1.0000
  16.500   1.2014   0.14119   0.13636  -0.0574   0.0403   1.0000
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