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GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 328 AIRFOIL (goe328-il)
Reynolds number: 200,000
Max Cl/Cd: 75.23 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe328-il-200000.txt
Download as CSV file: xf-goe328-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 328 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3752   0.10681   0.10322  -0.0158   1.0000   0.0373
  -8.500  -0.3756   0.10499   0.10145  -0.0208   1.0000   0.0378
  -8.250  -0.3755   0.10270   0.09922  -0.0252   1.0000   0.0380
  -8.000  -0.3690   0.09958   0.09613  -0.0310   1.0000   0.0381
  -7.750  -0.3631   0.09435   0.09094  -0.0312   1.0000   0.0385
  -7.500  -0.3542   0.09026   0.08686  -0.0274   1.0000   0.0390
  -7.250  -0.3450   0.08707   0.08369  -0.0266   1.0000   0.0397
  -7.000  -0.3370   0.08417   0.08083  -0.0273   1.0000   0.0406
  -6.750  -0.3309   0.08144   0.07814  -0.0286   1.0000   0.0416
  -6.500  -0.3302   0.07913   0.07589  -0.0290   1.0000   0.0424
  -6.250  -0.3390   0.07763   0.07446  -0.0274   1.0000   0.0429
  -6.000  -0.3371   0.07534   0.07219  -0.0286   0.9982   0.0438
  -5.750  -0.2723   0.07004   0.06659  -0.0494   0.9900   0.0473
  -5.500  -0.2339   0.06364   0.06001  -0.0586   0.9846   0.0480
  -5.250  -0.2122   0.05897   0.05539  -0.0603   0.9796   0.0490
  -5.000  -0.1818   0.05552   0.05194  -0.0637   0.9742   0.0507
  -4.750  -0.1415   0.05174   0.04806  -0.0699   0.9701   0.0534
  -4.500  -0.0840   0.04934   0.04510  -0.0792   0.9606   0.0590
  -4.250  -0.0520   0.04363   0.03927  -0.0838   0.9542   0.0604
  -4.000  -0.0270   0.04055   0.03623  -0.0853   0.9436   0.0618
  -3.750  -0.0005   0.03825   0.03387  -0.0865   0.9323   0.0640
  -3.500   0.0283   0.03613   0.03157  -0.0878   0.9217   0.0681
  -3.250   0.0611   0.03372   0.02871  -0.0894   0.9110   0.0746
  -3.000   0.0826   0.03170   0.02671  -0.0893   0.8991   0.0769
  -2.750   0.1074   0.03013   0.02501  -0.0892   0.8881   0.0810
  -2.500   0.1372   0.02856   0.02299  -0.0894   0.8785   0.0894
  -2.250   0.1604   0.02679   0.02124  -0.0893   0.8669   0.0927
  -2.000   0.1891   0.02577   0.01986  -0.0893   0.8563   0.1042
  -1.750   0.2131   0.02413   0.01822  -0.0891   0.8466   0.1091
  -1.500   0.2402   0.02292   0.01682  -0.0891   0.8356   0.1219
  -1.250   0.2667   0.02182   0.01560  -0.0891   0.8251   0.1371
  -1.000   0.2925   0.02103   0.01465  -0.0889   0.8154   0.1650
  -0.250   0.3888   0.01701   0.00926  -0.0861   0.7844   0.0737
   0.000   0.4161   0.01588   0.00804  -0.0856   0.7719   0.0703
   0.250   0.4435   0.01505   0.00708  -0.0850   0.7580   0.0685
   0.500   0.4708   0.01443   0.00636  -0.0844   0.7441   0.0682
   0.750   0.4982   0.01406   0.00591  -0.0839   0.7307   0.0707
   1.000   0.5255   0.01364   0.00544  -0.0835   0.7180   0.0715
   1.250   0.5529   0.01327   0.00504  -0.0831   0.7051   0.0723
   1.500   0.5802   0.01285   0.00461  -0.0827   0.6919   0.0744
   1.750   0.6077   0.01257   0.00433  -0.0825   0.6775   0.0791
   2.000   0.6352   0.01246   0.00416  -0.0822   0.6619   0.0873
   2.250   0.6629   0.01220   0.00399  -0.0820   0.6452   0.1268
   2.500   0.6837   0.01035   0.00387  -0.0802   0.6288   1.0000
   2.750   0.7108   0.01050   0.00387  -0.0798   0.6102   1.0000
   3.000   0.7377   0.01067   0.00391  -0.0795   0.5916   1.0000
   3.250   0.7646   0.01087   0.00396  -0.0793   0.5733   1.0000
   3.500   0.7915   0.01107   0.00407  -0.0790   0.5546   1.0000
   3.750   0.8184   0.01128   0.00420  -0.0788   0.5362   1.0000
   4.000   0.8451   0.01153   0.00436  -0.0786   0.5190   1.0000
   4.250   0.8717   0.01180   0.00454  -0.0783   0.5028   1.0000
   4.500   0.8983   0.01210   0.00477  -0.0781   0.4877   1.0000
   4.750   0.9247   0.01243   0.00503  -0.0779   0.4735   1.0000
   5.000   0.9511   0.01278   0.00532  -0.0777   0.4600   1.0000
   5.250   0.9773   0.01316   0.00565  -0.0774   0.4472   1.0000
   5.500   1.0035   0.01358   0.00601  -0.0772   0.4351   1.0000
   5.750   1.0293   0.01398   0.00635  -0.0769   0.4217   1.0000
   6.000   1.0548   0.01433   0.00669  -0.0766   0.4071   1.0000
   6.250   1.0801   0.01464   0.00704  -0.0763   0.3925   1.0000
   6.500   1.1049   0.01494   0.00732  -0.0758   0.3761   1.0000
   6.750   1.1295   0.01515   0.00759  -0.0754   0.3581   1.0000
   7.000   1.1543   0.01541   0.00790  -0.0750   0.3419   1.0000
   7.250   1.1788   0.01567   0.00824  -0.0745   0.3238   1.0000
   7.500   1.2021   0.01599   0.00855  -0.0739   0.2984   1.0000
   7.750   1.2232   0.01655   0.00899  -0.0730   0.2549   1.0000
   8.000   1.2233   0.01970   0.01092  -0.0700   0.0789   1.0000
   8.250   1.2350   0.02153   0.01262  -0.0679   0.0573   1.0000
   8.500   1.2496   0.02283   0.01405  -0.0662   0.0505   1.0000
   8.750   1.2579   0.02455   0.01584  -0.0637   0.0466   1.0000
   9.000   1.2710   0.02577   0.01717  -0.0617   0.0436   1.0000
   9.250   1.2813   0.02713   0.01857  -0.0596   0.0408   1.0000
   9.500   1.2847   0.02893   0.02037  -0.0566   0.0388   1.0000
   9.750   1.2893   0.03074   0.02224  -0.0537   0.0375   1.0000
  10.000   1.2999   0.03214   0.02375  -0.0516   0.0364   1.0000
  10.250   1.3113   0.03369   0.02538  -0.0496   0.0352   1.0000
  10.500   1.3241   0.03528   0.02705  -0.0480   0.0340   1.0000
  10.750   1.3365   0.03687   0.02870  -0.0464   0.0327   1.0000
  11.000   1.3502   0.03866   0.03048  -0.0451   0.0313   1.0000
  11.250   1.3812   0.04185   0.03370  -0.0454   0.0300   1.0000
  11.500   1.3939   0.04375   0.03582  -0.0438   0.0296   1.0000
  11.750   1.4068   0.04603   0.03833  -0.0423   0.0293   1.0000
  12.000   1.4176   0.04864   0.04119  -0.0407   0.0290   1.0000
  12.250   1.4243   0.05148   0.04430  -0.0389   0.0289   1.0000
  12.500   1.4251   0.05433   0.04742  -0.0368   0.0287   1.0000
  12.750   1.4218   0.05728   0.05063  -0.0348   0.0284   1.0000
  13.000   1.4156   0.06044   0.05406  -0.0330   0.0282   1.0000
  13.250   1.4067   0.06390   0.05778  -0.0315   0.0280   1.0000
  13.500   1.3956   0.06784   0.06197  -0.0305   0.0280   1.0000
  13.750   1.3817   0.07218   0.06656  -0.0299   0.0281   1.0000
  14.000   1.3660   0.07703   0.07166  -0.0300   0.0283   1.0000
  14.250   1.3488   0.08223   0.07708  -0.0306   0.0286   1.0000
  14.500   1.3306   0.08784   0.08290  -0.0318   0.0289   1.0000
  14.750   1.3118   0.09383   0.08907  -0.0335   0.0292   1.0000
  15.000   1.2935   0.10025   0.09566  -0.0356   0.0295   1.0000
  15.250   1.2977   0.10436   0.09987  -0.0357   0.0307   1.0000
  15.500   1.2571   0.11320   0.10906  -0.0423   0.0314   1.0000
  15.750   1.1787   0.13398   0.13034  -0.0586   0.0334   1.0000
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