XFOIL         Version 6.94
  
 Calculated polar for: S2048                                           
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.2925   0.00606   0.00200  -0.0696  0.8721  0.8300
   0.500   0.3448   0.00595   0.00193  -0.0683  0.8507  0.8642
   1.000   0.3949   0.00587   0.00189  -0.0665  0.8272  0.9064
   1.500   0.4543   0.00582   0.00187  -0.0666  0.8013  0.9625
   2.000   0.5266   0.00588   0.00185  -0.0702  0.7703  1.0000
   2.500   0.5776   0.00608   0.00194  -0.0691  0.7315  1.0000
   3.000   0.6272   0.00639   0.00205  -0.0676  0.6694  1.0000
   3.500   0.6696   0.00721   0.00230  -0.0648  0.5310  1.0000
   4.000   0.7119   0.00833   0.00279  -0.0624  0.3947  1.0000
   4.500   0.7583   0.00926   0.00333  -0.0610  0.3029  1.0000
   5.000   0.8064   0.01007   0.00392  -0.0598  0.2385  1.0000
   5.500   0.8549   0.01087   0.00453  -0.0587  0.1825  1.0000
   6.000   0.8991   0.01215   0.00537  -0.0570  0.0943  1.0000
   6.500   0.9431   0.01352   0.00653  -0.0552  0.0518  1.0000
   7.000   0.9895   0.01457   0.00766  -0.0537  0.0365  1.0000
   7.500   1.0348   0.01573   0.00883  -0.0521  0.0213  1.0000
   8.000   1.0719   0.01792   0.01114  -0.0490  0.0118  1.0000
  10.000   1.1970   0.02873   0.02319  -0.0348  0.0072  1.0000
  10.500   1.2055   0.03331   0.02824  -0.0289  0.0067  1.0000
  11.000   1.1871   0.03981   0.03535  -0.0210  0.0064  1.0000
  11.500   1.1586   0.04681   0.04289  -0.0152  0.0064  1.0000
  12.000   1.1326   0.05414   0.05064  -0.0131  0.0064  1.0000
  12.500   1.0972   0.06444   0.06134  -0.0155  0.0064  1.0000
  13.000   1.0670   0.07689   0.07411  -0.0227  0.0065  1.0000
  13.500   1.0399   0.09232   0.08983  -0.0334  0.0066  1.0000