XFOIL         Version 6.94
  
 Calculated polar for: SIKORSKY DBLN-526 AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.500   0.5942   0.01710   0.01195  -0.1333  0.8236  0.8696
   1.000   0.6779   0.01682   0.01165  -0.1408  0.8206  0.8861
   1.500   0.6989   0.01808   0.01296  -0.1334  0.8090  0.9015
   2.000   0.7734   0.01783   0.01265  -0.1390  0.8012  0.9139
   2.500   0.8682   0.01739   0.01212  -0.1500  0.7961  0.9242
   3.000   0.8693   0.01899   0.01382  -0.1378  0.7832  0.9349
   3.500   0.9367   0.01900   0.01380  -0.1418  0.7764  0.9433
   4.000   0.9787   0.01980   0.01465  -0.1399  0.7669  0.9517
   4.500   1.0251   0.02043   0.01527  -0.1388  0.7547  0.9610
   5.000   1.0662   0.02109   0.01595  -0.1367  0.7416  0.9679
   5.500   1.1270   0.02123   0.01600  -0.1391  0.7264  0.9775
   6.000   1.1524   0.02233   0.01703  -0.1333  0.6993  0.9845
   6.500   1.1722   0.02391   0.01861  -0.1266  0.6706  0.9889
   7.000   1.1791   0.02594   0.02043  -0.1172  0.6069  0.9944
   7.500   1.1850   0.02830   0.02247  -0.1082  0.5562  0.9970
   8.500   1.2245   0.03066   0.02471  -0.0969  0.5066  1.0000
   9.000   1.2482   0.03202   0.02607  -0.0922  0.4867  1.0000
   9.500   1.2237   0.03675   0.03035  -0.0790  0.3917  1.0000
  10.000   1.2300   0.04038   0.03375  -0.0724  0.3417  1.0000