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AUGUST 160 (august160-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AUGUST 160 (august160-il)
Reynolds number: 200,000
Max Cl/Cd: 42.45 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-august160-il-200000.txt
Download as CSV file: xf-august160-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AUGUST 160                                      
  
 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  -0.1356   0.09379   0.08882  -0.0505   0.5676   0.0487
  -9.250  -0.1328   0.09075   0.08578  -0.0518   0.5598   0.0502
  -9.000  -0.1480   0.08619   0.08127  -0.0569   0.5565   0.0520
  -8.750  -0.1582   0.08132   0.07645  -0.0604   0.5522   0.0526
  -8.500  -0.1396   0.07989   0.07492  -0.0577   0.5418   0.0535
  -8.250  -0.1350   0.07723   0.07227  -0.0581   0.5344   0.0542
  -8.000  -0.1353   0.07421   0.06920  -0.0593   0.5287   0.0557
  -7.750  -0.1471   0.07022   0.06523  -0.0622   0.5249   0.0571
  -7.500  -0.1638   0.06660   0.06160  -0.0632   0.5211   0.0579
  -7.250  -0.1919   0.06089   0.05568  -0.0648   0.5203   0.0597
  -7.000  -0.1777   0.05894   0.05374  -0.0637   0.5129   0.0604
  -6.750  -0.1676   0.05702   0.05171  -0.0628   0.5071   0.0618
  -6.500  -0.1849   0.05264   0.04683  -0.0618   0.5051   0.0671
  -6.250  -0.1651   0.05036   0.04470  -0.0613   0.4977   0.0681
  -6.000  -0.1503   0.04862   0.04290  -0.0603   0.4918   0.0700
  -5.750  -0.1461   0.04571   0.03959  -0.0588   0.4878   0.0762
  -5.500  -0.1277   0.04417   0.03813  -0.0579   0.4813   0.0790
  -5.250  -0.1171   0.04179   0.03548  -0.0564   0.4765   0.0857
  -5.000  -0.1048   0.04018   0.03347  -0.0545   0.4721   0.0939
  -4.750  -0.0846   0.03823   0.03156  -0.0539   0.4670   0.0962
  -4.500  -0.0690   0.03652   0.02961  -0.0523   0.4623   0.1047
  -4.250  -0.0512   0.02678   0.01820  -0.0464   0.4609   0.0445
  -4.000  -0.0276   0.02469   0.01545  -0.0444   0.4564   0.0402
  -3.750  -0.0019   0.02342   0.01398  -0.0436   0.4522   0.0397
  -3.500   0.0243   0.02240   0.01277  -0.0428   0.4480   0.0395
  -3.250   0.0508   0.02150   0.01174  -0.0421   0.4434   0.0397
  -3.000   0.0776   0.02084   0.01091  -0.0414   0.4391   0.0404
  -2.750   0.1035   0.02013   0.01023  -0.0409   0.4354   0.0426
  -2.500   0.1297   0.01972   0.00972  -0.0403   0.4319   0.0441
  -2.250   0.1550   0.01927   0.00927  -0.0395   0.4284   0.0455
  -2.000   0.1790   0.01877   0.00882  -0.0385   0.4248   0.0469
  -1.750   0.2029   0.01839   0.00848  -0.0375   0.4213   0.0496
  -1.500   0.2270   0.01805   0.00810  -0.0366   0.4180   0.0540
  -1.250   0.2511   0.01774   0.00774  -0.0356   0.4150   0.0639
  -0.750   0.3081   0.01506   0.00822  -0.0347   0.4089   0.9021
  -0.500   0.4669   0.01609   0.00886  -0.0582   0.4020   0.9850
  -0.250   0.5323   0.01610   0.00862  -0.0657   0.3985   0.9972
   0.000   0.5653   0.01623   0.00857  -0.0670   0.3960   1.0000
   0.250   0.5874   0.01655   0.00877  -0.0661   0.3939   1.0000
   0.500   0.6088   0.01670   0.00891  -0.0651   0.3919   1.0000
   0.750   0.6303   0.01689   0.00910  -0.0640   0.3897   1.0000
   1.000   0.6521   0.01711   0.00929  -0.0631   0.3876   1.0000
   1.250   0.6739   0.01734   0.00948  -0.0621   0.3854   1.0000
   1.500   0.6959   0.01758   0.00967  -0.0611   0.3834   1.0000
   1.750   0.7181   0.01783   0.00986  -0.0602   0.3817   1.0000
   2.000   0.7406   0.01807   0.01002  -0.0593   0.3799   1.0000
   2.250   0.7633   0.01838   0.01023  -0.0585   0.3780   1.0000
   2.500   0.7855   0.01896   0.01073  -0.0577   0.3761   1.0000
   2.750   0.8057   0.01931   0.01114  -0.0564   0.3748   1.0000
   3.000   0.8256   0.01972   0.01160  -0.0552   0.3732   1.0000
   3.250   0.8455   0.02016   0.01209  -0.0540   0.3716   1.0000
   3.500   0.8653   0.02063   0.01260  -0.0527   0.3699   1.0000
   3.750   0.8851   0.02108   0.01307  -0.0515   0.3682   1.0000
   4.000   0.9051   0.02150   0.01351  -0.0503   0.3665   1.0000
   4.250   0.9254   0.02188   0.01389  -0.0491   0.3648   1.0000
   4.500   0.9458   0.02230   0.01431  -0.0480   0.3633   1.0000
   4.750   0.9662   0.02276   0.01476  -0.0469   0.3621   1.0000
   5.000   0.9870   0.02325   0.01522  -0.0458   0.3609   1.0000
   5.250   1.0082   0.02382   0.01576  -0.0449   0.3596   1.0000
   5.500   1.0268   0.02471   0.01666  -0.0437   0.3581   1.0000
   5.750   1.0398   0.02540   0.01750  -0.0416   0.3567   1.0000
   6.000   1.0521   0.02625   0.01849  -0.0395   0.3552   1.0000
   6.250   1.0637   0.02721   0.01957  -0.0373   0.3537   1.0000
   6.500   1.0751   0.02820   0.02067  -0.0352   0.3521   1.0000
   6.750   1.0868   0.02921   0.02179  -0.0332   0.3506   1.0000
   7.000   1.0993   0.03018   0.02284  -0.0313   0.3492   1.0000
   7.250   1.1128   0.03111   0.02384  -0.0296   0.3479   1.0000
   7.500   1.1278   0.03199   0.02476  -0.0282   0.3467   1.0000
   7.750   1.1433   0.03283   0.02565  -0.0268   0.3455   1.0000
   8.000   1.1603   0.03361   0.02646  -0.0257   0.3444   1.0000
   8.250   1.1786   0.03441   0.02727  -0.0247   0.3433   1.0000
   8.500   1.2009   0.03511   0.02796  -0.0242   0.3422   1.0000
   8.750   1.1991   0.03726   0.03025  -0.0214   0.3405   1.0000
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