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NREL's S806A Airfoil (modified line 35) (s806a-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S806A Airfoil (modified line 35) (s806a-nr)
Reynolds number: 100,000
Max Cl/Cd: 53.32 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s806a-nr-100000.txt
Download as CSV file: xf-s806a-nr-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4417   0.12228   0.11769  -0.0361   1.0000   0.0795
 -10.000  -0.4457   0.11912   0.11459  -0.0419   1.0000   0.0798
  -9.750  -0.4512   0.11566   0.11117  -0.0475   1.0000   0.0800
  -2.250  -0.0210   0.02731   0.01716  -0.0672   0.9119   0.0480
  -2.000   0.0038   0.02675   0.01658  -0.0670   0.9095   0.0475
  -1.750   0.1663   0.02197   0.01523  -0.0848   0.9171   1.0000
  -1.500   0.1483   0.02261   0.01582  -0.0776   0.9111   1.0000
  -1.250   0.1516   0.02303   0.01612  -0.0742   0.9068   1.0000
  -1.000   0.1796   0.02328   0.01618  -0.0750   0.9031   1.0000
  -0.750   0.2215   0.02354   0.01626  -0.0783   0.9003   1.0000
  -0.500   0.1560   0.02430   0.01706  -0.0625   0.8931   1.0000
  -0.250   0.1554   0.02480   0.01747  -0.0585   0.8892   1.0000
   0.000   0.1668   0.02531   0.01787  -0.0566   0.8858   1.0000
   0.250   0.1841   0.02584   0.01830  -0.0558   0.8815   1.0000
   0.500   0.2088   0.02632   0.01868  -0.0560   0.8755   1.0000
   0.750   0.2380   0.02681   0.01908  -0.0570   0.8699   1.0000
   1.000   0.2674   0.02740   0.01959  -0.0582   0.8660   1.0000
   1.250   0.2998   0.02803   0.02017  -0.0599   0.8622   1.0000
   1.500   0.3376   0.02870   0.02065  -0.0623   0.8584   1.0000
   1.750   0.3835   0.02960   0.02163  -0.0659   0.8538   1.0000
   2.000   0.4040   0.03074   0.02275  -0.0654   0.8469   1.0000
   2.250   0.4035   0.03101   0.02300  -0.0618   0.8394   1.0000
   2.500   0.4159   0.03152   0.02351  -0.0602   0.8312   1.0000
   2.750   0.4412   0.03194   0.02393  -0.0603   0.8222   1.0000
   3.000   0.4762   0.03230   0.02432  -0.0617   0.8146   1.0000
   3.250   0.5198   0.03268   0.02474  -0.0643   0.8086   1.0000
   3.500   0.5740   0.03318   0.02532  -0.0683   0.8032   1.0000
   3.750   0.5655   0.03405   0.02621  -0.0635   0.7893   1.0000
   4.000   0.5772   0.03448   0.02668  -0.0615   0.7763   1.0000
   4.250   0.6131   0.03439   0.02669  -0.0623   0.7660   1.0000
   4.500   0.6705   0.03364   0.02608  -0.0654   0.7584   1.0000
   4.750   0.7308   0.03270   0.02543  -0.0682   0.7519   1.0000
   5.000   0.7153   0.03396   0.02673  -0.0635   0.7302   1.0000
   5.250   0.7565   0.03280   0.02573  -0.0637   0.7174   1.0000
   5.500   0.8126   0.03004   0.02318  -0.0635   0.7080   1.0000
   5.750   0.8773   0.01994   0.01297  -0.0554   0.6384   1.0000
   6.000   0.8909   0.02759   0.02094  -0.0649   0.6790   1.0000
   6.250   0.9310   0.02507   0.01859  -0.0635   0.6639   1.0000
   6.500   0.9746   0.02188   0.01552  -0.0616   0.6461   1.0000
   6.750   0.9984   0.02048   0.01429  -0.0592   0.6058   1.0000
   7.000   1.0232   0.01919   0.01288  -0.0564   0.5235   1.0000
   7.250   1.0297   0.01994   0.01222  -0.0513   0.3475   1.0000
   7.500   1.0269   0.02224   0.01367  -0.0474   0.2396   1.0000
   7.750   1.0248   0.02455   0.01562  -0.0438   0.1643   1.0000
   8.000   1.0285   0.02643   0.01714  -0.0410   0.1248   1.0000
   8.250   1.0322   0.02813   0.01860  -0.0382   0.1028   1.0000
   8.500   1.0414   0.02982   0.02021  -0.0359   0.0871   1.0000
   8.750   1.0550   0.03174   0.02204  -0.0340   0.0757   1.0000
   9.000   1.0718   0.03322   0.02355  -0.0327   0.0666   1.0000
   9.250   1.1022   0.03588   0.02618  -0.0329   0.0580   1.0000
   9.500   1.1273   0.03759   0.02801  -0.0326   0.0538   1.0000
   9.750   1.1561   0.03980   0.03022  -0.0330   0.0511   1.0000
  10.000   1.1914   0.04360   0.03417  -0.0342   0.0497   1.0000
  10.250   1.2116   0.04673   0.03768  -0.0334   0.0494   1.0000
  10.500   1.2273   0.05025   0.04167  -0.0323   0.0494   1.0000
  10.750   1.2404   0.05428   0.04604  -0.0311   0.0497   1.0000
  11.000   1.2479   0.05756   0.04971  -0.0292   0.0503   1.0000
  11.250   1.2381   0.06048   0.05322  -0.0252   0.0514   1.0000
  11.500   1.2068   0.06458   0.05791  -0.0197   0.0529   1.0000
  11.750   1.1797   0.06923   0.06296  -0.0163   0.0541   1.0000
  12.000   1.1542   0.07413   0.06818  -0.0141   0.0551   1.0000
  12.250   1.1288   0.07939   0.07369  -0.0129   0.0561   1.0000
  12.500   1.1027   0.08505   0.07957  -0.0126   0.0569   1.0000
  12.750   1.0757   0.09134   0.08604  -0.0132   0.0577   1.0000
  13.000   1.0484   0.09840   0.09324  -0.0147   0.0586   1.0000
  13.250   1.0475   0.10363   0.09859  -0.0153   0.0610   1.0000
  13.500   1.0137   0.11095   0.10605  -0.0197   0.0623   1.0000
  13.750   0.9348   0.13912   0.13437  -0.0365   0.0821   1.0000
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