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GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 795 AIRFOIL (goe795-il)
Reynolds number: 200,000
Max Cl/Cd: 75.39 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe795-il-200000.txt
Download as CSV file: xf-goe795-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 795 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4634   0.13110   0.12727  -0.0167   1.0000   0.0371
 -11.250  -0.4693   0.12891   0.12513  -0.0211   1.0000   0.0383
 -11.000  -0.4683   0.12561   0.12187  -0.0233   1.0000   0.0385
 -10.750  -0.4658   0.12194   0.11822  -0.0248   1.0000   0.0386
 -10.500  -0.4652   0.11516   0.11148  -0.0240   1.0000   0.0399
 -10.250  -0.4538   0.11205   0.10836  -0.0222   1.0000   0.0414
 -10.000  -0.4482   0.10904   0.10536  -0.0222   1.0000   0.0435
  -9.750  -0.4454   0.10594   0.10228  -0.0230   1.0000   0.0464
  -9.500  -0.4468   0.10257   0.09894  -0.0252   1.0000   0.0492
  -9.250  -0.3850   0.08864   0.08534  -0.0341   1.0000   0.0522
  -9.000  -0.3708   0.08569   0.08236  -0.0313   1.0000   0.0538
  -8.750  -0.3669   0.08260   0.07930  -0.0307   1.0000   0.0554
  -8.500  -0.3673   0.07926   0.07595  -0.0309   1.0000   0.0571
  -8.250  -0.4707   0.08374   0.08040  -0.0329   1.0000   0.0530
  -8.000  -0.4673   0.08140   0.07809  -0.0311   1.0000   0.0542
  -7.750  -0.4706   0.07883   0.07556  -0.0304   1.0000   0.0554
  -7.500  -0.4726   0.07568   0.07244  -0.0311   1.0000   0.0569
  -7.250  -0.4758   0.07215   0.06893  -0.0324   1.0000   0.0589
  -7.000  -0.4793   0.06809   0.06485  -0.0345   1.0000   0.0610
  -6.750  -0.4905   0.06291   0.05923  -0.0400   1.0000   0.0639
  -6.500  -0.4909   0.05733   0.05379  -0.0385   1.0000   0.0652
  -6.250  -0.4833   0.05569   0.05224  -0.0357   1.0000   0.0667
  -6.000  -0.4759   0.05427   0.05080  -0.0335   1.0000   0.0698
  -5.500  -0.4520   0.03578   0.03222  -0.0310   1.0000   0.0788
  -5.250  -0.4409   0.03339   0.02982  -0.0300   0.9993   0.0804
  -5.000  -0.4537   0.03224   0.02702  -0.0293   1.0000   0.0531
  -4.750  -0.4393   0.02867   0.02321  -0.0273   1.0000   0.0454
  -4.500  -0.4093   0.02375   0.01717  -0.0271   0.9972   0.0395
  -4.250  -0.3731   0.02204   0.01509  -0.0288   0.9934   0.0390
  -4.000  -0.3402   0.01984   0.01250  -0.0299   0.9891   0.0393
  -3.750  -0.3062   0.01773   0.01014  -0.0311   0.9853   0.0415
  -3.500  -0.2681   0.01672   0.00906  -0.0333   0.9818   0.0451
  -3.250  -0.2349   0.01593   0.00811  -0.0343   0.9752   0.0508
  -3.000  -0.1980   0.01499   0.00724  -0.0362   0.9707   0.0662
  -2.750  -0.1634   0.01456   0.00683  -0.0377   0.9644   0.0861
  -2.500  -0.1271   0.01397   0.00630  -0.0395   0.9589   0.1116
  -2.250  -0.0902   0.01347   0.00594  -0.0416   0.9541   0.1509
  -2.000  -0.0570   0.01312   0.00577  -0.0429   0.9469   0.1985
  -1.750  -0.0183   0.01256   0.00551  -0.0454   0.9432   0.2714
  -1.500   0.0066   0.01169   0.00539  -0.0452   0.9348   0.4471
  -1.250   0.1202   0.01045   0.00562  -0.0629   0.9504   1.0000
  -1.000   0.1645   0.01032   0.00534  -0.0662   0.9451   1.0000
  -0.750   0.2098   0.01011   0.00500  -0.0697   0.9392   1.0000
  -0.500   0.2554   0.00986   0.00466  -0.0732   0.9321   1.0000
  -0.250   0.2979   0.00962   0.00434  -0.0760   0.9237   1.0000
   0.000   0.3402   0.00938   0.00404  -0.0787   0.9159   1.0000
   0.250   0.3731   0.00928   0.00388  -0.0796   0.9047   1.0000
   0.500   0.4055   0.00919   0.00376  -0.0804   0.8940   1.0000
   0.750   0.4374   0.00912   0.00366  -0.0810   0.8833   1.0000
   1.000   0.4679   0.00907   0.00357  -0.0813   0.8719   1.0000
   1.250   0.4964   0.00905   0.00351  -0.0812   0.8595   1.0000
   1.500   0.5219   0.00906   0.00348  -0.0803   0.8445   1.0000
   1.750   0.5459   0.00906   0.00346  -0.0791   0.8262   1.0000
   2.000   0.5710   0.00905   0.00337  -0.0780   0.8062   1.0000
   2.250   0.5942   0.00910   0.00336  -0.0766   0.7852   1.0000
   2.500   0.6182   0.00917   0.00339  -0.0754   0.7665   1.0000
   2.750   0.6418   0.00927   0.00344  -0.0742   0.7470   1.0000
   3.000   0.6645   0.00939   0.00355  -0.0728   0.7259   1.0000
   3.250   0.6871   0.00953   0.00364  -0.0714   0.7037   1.0000
   3.500   0.7091   0.00968   0.00373  -0.0698   0.6789   1.0000
   3.750   0.7300   0.00983   0.00384  -0.0680   0.6498   1.0000
   4.000   0.7504   0.01000   0.00396  -0.0662   0.6164   1.0000
   4.250   0.7705   0.01022   0.00413  -0.0643   0.5789   1.0000
   4.500   0.7888   0.01054   0.00428  -0.0621   0.5290   1.0000
   4.750   0.8063   0.01095   0.00450  -0.0599   0.4754   1.0000
   5.000   0.8229   0.01148   0.00479  -0.0576   0.4215   1.0000
   5.250   0.8393   0.01207   0.00517  -0.0553   0.3712   1.0000
   5.500   0.8554   0.01272   0.00562  -0.0531   0.3201   1.0000
   5.750   0.8702   0.01351   0.00616  -0.0507   0.2443   1.0000
   6.000   0.8788   0.01491   0.00695  -0.0475   0.1495   1.0000
   6.250   0.8922   0.01602   0.00783  -0.0450   0.1138   1.0000
   6.500   0.9090   0.01683   0.00859  -0.0429   0.0991   1.0000
   6.750   0.9265   0.01757   0.00929  -0.0412   0.0876   1.0000
   7.000   0.9442   0.01827   0.00996  -0.0396   0.0763   1.0000
   7.250   0.9640   0.01881   0.01061  -0.0381   0.0675   1.0000
   7.500   0.9805   0.01963   0.01141  -0.0364   0.0538   1.0000
   7.750   0.9890   0.02146   0.01332  -0.0330   0.0367   1.0000
   8.000   1.0012   0.02292   0.01477  -0.0305   0.0290   1.0000
   8.250   1.0202   0.02347   0.01542  -0.0289   0.0231   1.0000
   8.500   1.0306   0.02576   0.01773  -0.0263   0.0208   1.0000
   8.750   1.0484   0.02742   0.01957  -0.0245   0.0198   1.0000
   9.000   1.0665   0.02961   0.02199  -0.0229   0.0190   1.0000
   9.250   1.0834   0.03216   0.02483  -0.0212   0.0184   1.0000
   9.500   1.0968   0.03510   0.02813  -0.0190   0.0182   1.0000
   9.750   1.1045   0.03847   0.03191  -0.0163   0.0182   1.0000
  10.000   1.1067   0.04185   0.03568  -0.0131   0.0184   1.0000
  10.250   1.1038   0.04517   0.03937  -0.0095   0.0183   1.0000
  10.500   1.0956   0.04817   0.04267  -0.0054   0.0183   1.0000
  10.750   1.0847   0.05066   0.04542  -0.0013   0.0176   1.0000
  11.000   1.0721   0.05340   0.04844   0.0020   0.0173   1.0000
  11.250   1.0575   0.05648   0.05174   0.0045   0.0170   1.0000
  11.500   1.0327   0.06136   0.05685   0.0061   0.0179   1.0000
  11.750   1.0139   0.06561   0.06130   0.0062   0.0178   1.0000
  12.000   0.9898   0.07148   0.06733   0.0049   0.0191   1.0000
  12.250   0.9680   0.07744   0.07345   0.0023   0.0193   1.0000
  12.500   0.9460   0.08442   0.08052  -0.0011   0.0202   1.0000
  12.750   0.9239   0.09228   0.08856  -0.0070   0.0197   1.0000
  13.000   0.8073   0.09608   0.09257  -0.0053   0.0204   1.0000
  13.250   0.7822   0.10508   0.10164  -0.0104   0.0207   1.0000
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