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NREL's S806A Airfoil (modified line 35) (s806a-nr) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NREL's S806A Airfoil (modified line 35) (s806a-nr)
Reynolds number: 50,000
Max Cl/Cd: 34.4 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s806a-nr-50000.txt
Download as CSV file: xf-s806a-nr-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S806A Airfoil                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3913   0.11167   0.10514  -0.0268   1.0000   0.2400
  -8.750  -0.4246   0.11528   0.10894  -0.0298   1.0000   0.2474
  -8.500  -0.4605   0.11736   0.11119  -0.0274   1.0000   0.2486
  -8.250  -0.3781   0.10152   0.09520  -0.0263   1.0000   0.2718
  -8.000  -0.3870   0.10054   0.09431  -0.0241   1.0000   0.2841
  -7.750  -0.4193   0.10176   0.09567  -0.0202   1.0000   0.2914
  -7.500  -0.4618   0.10378   0.09784  -0.0154   1.0000   0.2949
  -7.250  -0.5077   0.10602   0.10022  -0.0121   1.0000   0.2975
  -7.000  -0.4334   0.09486   0.08898  -0.0102   1.0000   0.3293
  -6.750  -0.4654   0.09536   0.08960  -0.0056   1.0000   0.3391
  -6.500  -0.5164   0.09753   0.09192  -0.0021   1.0000   0.3459
  -5.750  -0.4760   0.08690   0.08142   0.0104   1.0000   0.4344
  -5.500  -0.4574   0.08411   0.07866   0.0144   1.0000   0.4819
  -5.250  -0.4233   0.08388   0.07844   0.0169   1.0000   0.5343
  -4.000  -0.3976   0.06941   0.06424   0.0312   1.0000   0.6753
  -3.750  -0.4423   0.05351   0.04612  -0.0252   1.0000   0.1942
  -3.500  -0.4070   0.04967   0.04149  -0.0273   1.0000   0.1459
  -3.250  -0.3747   0.04618   0.03693  -0.0285   1.0000   0.1205
  -3.000  -0.3501   0.04187   0.03241  -0.0293   1.0000   0.1126
  -2.750  -0.3243   0.03957   0.02965  -0.0293   1.0000   0.1063
  -1.250  -0.1870   0.03391   0.02268  -0.0256   1.0000   0.1066
  -1.000  -0.1587   0.03300   0.02161  -0.0248   1.0000   0.1086
  -0.750  -0.1299   0.03235   0.02078  -0.0244   1.0000   0.1153
  -0.500  -0.0979   0.03142   0.01975  -0.0249   1.0000   0.1377
  -0.250  -0.0831   0.02774   0.01894  -0.0186   1.0000   1.0000
   0.000  -0.0600   0.02823   0.01879  -0.0183   1.0000   1.0000
   0.250  -0.0373   0.02876   0.01893  -0.0184   1.0000   1.0000
   0.500  -0.0148   0.02933   0.01922  -0.0186   1.0000   1.0000
   0.750   0.0077   0.02994   0.01958  -0.0189   1.0000   1.0000
   1.000   0.0304   0.03060   0.01999  -0.0193   1.0000   1.0000
   1.250   0.0525   0.03129   0.02053  -0.0196   1.0000   1.0000
   1.500   0.0746   0.03203   0.02112  -0.0200   1.0000   1.0000
   1.750   0.0964   0.03282   0.02178  -0.0205   1.0000   1.0000
   2.000   0.1181   0.03365   0.02252  -0.0209   1.0000   1.0000
   2.250   0.1395   0.03454   0.02331  -0.0214   1.0000   1.0000
   2.500   0.1606   0.03547   0.02419  -0.0219   1.0000   1.0000
   3.000   0.2010   0.03749   0.02611  -0.0228   1.0000   1.0000
   3.250   0.2195   0.03856   0.02717  -0.0230   1.0000   1.0000
   3.500   0.2376   0.03970   0.02830  -0.0233   1.0000   1.0000
   3.750   0.2551   0.04088   0.02950  -0.0235   1.0000   1.0000
   4.000   0.2722   0.04213   0.03079  -0.0238   1.0000   1.0000
   4.250   0.2886   0.04344   0.03214  -0.0240   1.0000   1.0000
   4.500   0.3046   0.04484   0.03359  -0.0243   1.0000   1.0000
   4.750   0.3200   0.04631   0.03513  -0.0246   1.0000   1.0000
   5.000   0.3348   0.04788   0.03677  -0.0250   1.0000   1.0000
   5.250   0.3488   0.04952   0.03852  -0.0253   1.0000   1.0000
   5.500   0.5407   0.05328   0.04279  -0.0499   0.8374   1.0000
   5.750   0.5838   0.05412   0.04387  -0.0520   0.8096   1.0000
   6.000   0.7736   0.02775   0.01606  -0.0305   0.2491   1.0000
   6.250   0.7480   0.03154   0.01829  -0.0252   0.0779   1.0000
   6.500   0.7430   0.03432   0.02066  -0.0209   0.0469   1.0000
   6.750   0.7855   0.05333   0.04414  -0.0606   0.6943   1.0000
   7.000   0.8148   0.05157   0.04265  -0.0583   0.6605   1.0000
   7.250   0.8467   0.04964   0.04102  -0.0556   0.6266   1.0000
   7.500   0.9279   0.04156   0.03358  -0.0525   0.5893   1.0000
   7.750   1.0117   0.02941   0.02126  -0.0434   0.4471   1.0000
   8.000   1.0117   0.03130   0.02175  -0.0373   0.3194   1.0000
   8.250   1.0181   0.03470   0.02478  -0.0334   0.2298   1.0000
   8.500   1.0401   0.03742   0.02723  -0.0320   0.1787   1.0000
   8.750   1.0850   0.04202   0.03175  -0.0332   0.1456   1.0000
   9.000   1.0972   0.04328   0.03302  -0.0314   0.1301   1.0000
   9.250   1.1138   0.04582   0.03543  -0.0306   0.1146   1.0000
   9.500   1.1338   0.04814   0.03788  -0.0297   0.1058   1.0000
   9.750   1.1598   0.05245   0.04213  -0.0300   0.0992   1.0000
  10.000   1.1679   0.05574   0.04599  -0.0278   0.0966   1.0000
  10.250   1.1720   0.05948   0.05022  -0.0256   0.0949   1.0000
  10.500   1.1708   0.06342   0.05459  -0.0232   0.0940   1.0000
  10.750   1.1642   0.06747   0.05903  -0.0207   0.0938   1.0000
  11.000   1.1520   0.07153   0.06341  -0.0180   0.0940   1.0000
  11.250   1.1346   0.07558   0.06773  -0.0153   0.0945   1.0000
  11.500   1.1148   0.08003   0.07242  -0.0135   0.0951   1.0000
  11.750   1.0936   0.08493   0.07752  -0.0125   0.0958   1.0000
  12.000   1.0710   0.09030   0.08306  -0.0123   0.0966   1.0000
  12.250   1.0492   0.09621   0.08911  -0.0129   0.0975   1.0000
  12.500   1.0301   0.10262   0.09562  -0.0141   0.0985   1.0000
  12.750   1.0223   0.10949   0.10253  -0.0152   0.0997   1.0000
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