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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 200,000
Max Cl/Cd: 81.15 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e176-il-200000.txt
Download as CSV file: xf-e176-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E176  (8.83%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4095   0.10752   0.10406  -0.0172   1.0000   0.0392
  -9.250  -0.4095   0.10475   0.10134  -0.0211   1.0000   0.0399
  -9.000  -0.4083   0.10156   0.09821  -0.0243   1.0000   0.0401
  -8.750  -0.4060   0.09826   0.09495  -0.0271   1.0000   0.0402
  -8.500  -0.4049   0.09473   0.09148  -0.0301   1.0000   0.0403
  -8.250  -0.3964   0.08862   0.08538  -0.0266   1.0000   0.0419
  -8.000  -0.3879   0.08572   0.08251  -0.0263   1.0000   0.0430
  -7.750  -0.3832   0.08279   0.07962  -0.0272   1.0000   0.0440
  -7.500  -0.3811   0.07982   0.07670  -0.0282   1.0000   0.0456
  -7.250  -0.3799   0.07657   0.07352  -0.0305   1.0000   0.0469
  -7.000  -0.3758   0.07277   0.06977  -0.0345   1.0000   0.0485
  -6.750  -0.3711   0.06842   0.06546  -0.0402   1.0000   0.0505
  -6.500  -0.3631   0.06323   0.06002  -0.0516   0.9943   0.0525
  -6.250  -0.3414   0.05590   0.05275  -0.0563   0.9852   0.0543
  -6.000  -0.3121   0.05354   0.05042  -0.0583   0.9752   0.0580
  -5.750  -0.2717   0.04573   0.04195  -0.0707   0.9589   0.0668
  -5.500  -0.2441   0.04233   0.03862  -0.0727   0.9457   0.0690
  -5.250  -0.2168   0.03947   0.03560  -0.0747   0.9301   0.0734
  -5.000  -0.1940   0.03564   0.03129  -0.0765   0.9131   0.0818
  -4.750  -0.1733   0.03351   0.02907  -0.0761   0.8974   0.0853
  -4.500  -0.1522   0.03102   0.02616  -0.0760   0.8829   0.0959
  -4.250  -0.1207   0.02185   0.01542  -0.0737   0.8724   0.0385
  -4.000  -0.0962   0.01959   0.01275  -0.0728   0.8602   0.0372
  -3.750  -0.0706   0.01797   0.01076  -0.0719   0.8491   0.0370
  -3.500  -0.0445   0.01716   0.00967  -0.0711   0.8389   0.0391
  -3.250  -0.0184   0.01617   0.00846  -0.0703   0.8294   0.0399
  -3.000   0.0079   0.01517   0.00735  -0.0697   0.8193   0.0404
  -2.750   0.0328   0.01390   0.00603  -0.0689   0.8107   0.0428
  -2.500   0.0588   0.01329   0.00535  -0.0683   0.8020   0.0474
  -2.250   0.0853   0.01268   0.00470  -0.0679   0.7933   0.0596
  -2.000   0.1092   0.01138   0.00419  -0.0675   0.7861   0.2513
  -1.750   0.1325   0.01057   0.00414  -0.0670   0.7774   0.4620
  -1.500   0.1503   0.00971   0.00414  -0.0645   0.7709   0.7146
  -1.250   0.2090   0.00912   0.00392  -0.0696   0.7633   1.0000
  -1.000   0.2343   0.00923   0.00380  -0.0690   0.7567   1.0000
  -0.750   0.2603   0.00933   0.00375  -0.0687   0.7486   1.0000
  -0.500   0.2863   0.00945   0.00368  -0.0682   0.7424   1.0000
  -0.250   0.3127   0.00956   0.00369  -0.0680   0.7345   1.0000
   0.000   0.3390   0.00969   0.00365  -0.0675   0.7288   1.0000
   0.250   0.3656   0.00981   0.00371  -0.0674   0.7211   1.0000
   0.500   0.3923   0.00995   0.00371  -0.0670   0.7153   1.0000
   0.750   0.4191   0.01009   0.00381  -0.0669   0.7081   1.0000
   1.000   0.4459   0.01022   0.00385  -0.0666   0.7020   1.0000
   1.250   0.4727   0.01038   0.00397  -0.0664   0.6954   1.0000
   1.500   0.4996   0.01052   0.00405  -0.0662   0.6890   1.0000
   1.750   0.5266   0.01069   0.00417  -0.0660   0.6829   1.0000
   2.000   0.5535   0.01084   0.00431  -0.0658   0.6760   1.0000
   2.250   0.5805   0.01100   0.00442  -0.0656   0.6702   1.0000
   2.500   0.6073   0.01115   0.00459  -0.0654   0.6624   1.0000
   2.750   0.6343   0.01129   0.00468  -0.0651   0.6561   1.0000
   3.000   0.6609   0.01142   0.00487  -0.0649   0.6477   1.0000
   3.250   0.6877   0.01156   0.00499  -0.0646   0.6404   1.0000
   3.500   0.7144   0.01166   0.00510  -0.0642   0.6317   1.0000
   3.750   0.7409   0.01177   0.00525  -0.0639   0.6227   1.0000
   4.000   0.7679   0.01186   0.00533  -0.0635   0.6148   1.0000
   4.250   0.7941   0.01195   0.00551  -0.0632   0.6044   1.0000
   4.500   0.8205   0.01204   0.00565  -0.0628   0.5944   1.0000
   4.750   0.8470   0.01209   0.00572  -0.0624   0.5841   1.0000
   5.000   0.8733   0.01213   0.00581  -0.0619   0.5726   1.0000
   5.250   0.8993   0.01217   0.00594  -0.0614   0.5595   1.0000
   5.500   0.9251   0.01221   0.00605  -0.0608   0.5452   1.0000
   5.750   0.9504   0.01223   0.00615  -0.0602   0.5274   1.0000
   6.000   0.9748   0.01221   0.00618  -0.0593   0.5008   1.0000
   6.250   0.9981   0.01230   0.00626  -0.0583   0.4626   1.0000
   6.500   1.0197   0.01264   0.00645  -0.0572   0.4068   1.0000
   6.750   1.0360   0.01358   0.00691  -0.0556   0.3114   1.0000
   7.000   1.0489   0.01507   0.00784  -0.0540   0.2156   1.0000
   7.250   1.0618   0.01663   0.00895  -0.0524   0.1354   1.0000
   7.500   1.0645   0.01934   0.01087  -0.0496   0.0406   1.0000
   7.750   1.0767   0.02092   0.01250  -0.0474   0.0306   1.0000
   8.000   1.0925   0.02200   0.01368  -0.0459   0.0266   1.0000
   8.250   1.1033   0.02345   0.01519  -0.0439   0.0236   1.0000
   8.500   1.1101   0.02527   0.01709  -0.0413   0.0224   1.0000
   8.750   1.1219   0.02666   0.01859  -0.0393   0.0218   1.0000
   9.000   1.1331   0.02815   0.02018  -0.0372   0.0212   1.0000
   9.250   1.1465   0.02984   0.02200  -0.0353   0.0206   1.0000
   9.500   1.1639   0.03175   0.02402  -0.0340   0.0203   1.0000
   9.750   1.1848   0.03400   0.02645  -0.0332   0.0201   1.0000
  10.000   1.2065   0.03671   0.02940  -0.0325   0.0201   1.0000
  10.250   1.2241   0.03981   0.03280  -0.0315   0.0205   1.0000
  10.500   1.2356   0.04327   0.03660  -0.0300   0.0209   1.0000
  10.750   1.2403   0.04709   0.04075  -0.0281   0.0214   1.0000
  11.000   1.2388   0.05109   0.04506  -0.0259   0.0219   1.0000
  11.250   1.2323   0.05505   0.04929  -0.0236   0.0222   1.0000
  11.500   1.2294   0.06061   0.05510  -0.0224   0.0227   1.0000
  11.750   1.2240   0.06258   0.05724  -0.0205   0.0229   1.0000
  12.000   1.2150   0.06510   0.06000  -0.0192   0.0231   1.0000
  12.250   1.1974   0.06953   0.06466  -0.0188   0.0230   1.0000
  12.500   1.1840   0.07316   0.06849  -0.0189   0.0232   1.0000
  12.750   1.0371   0.07706   0.07314  -0.0175   0.0251   1.0000
  13.000   1.0006   0.08540   0.08174  -0.0208   0.0257   1.0000
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