Airfoil: S6062
Builder: B. Matheson
Comment: clean

Number of Reynolds #'s:
 3 

Average Reynolds #:
 101900 
Number of angles of attack:
 33 
 alpha /   Cl   /  Cm
 -5.76  -0.348  -0.0400
 -3.98  -0.199  -0.0400
 -2.27  -0.055  -0.0400
 -0.60   0.091  -0.0400
  0.68   0.232  -0.0400
  2.40   0.509  -0.0400
  3.55   0.620  -0.0400
  5.33   0.769  -0.0400
  7.05   0.877  -0.0400
  8.25   0.950  -0.0400
  9.82   1.024  -0.0400
 11.54   1.038  -0.0400
 12.67   1.000  -0.0400
 14.37   0.952  -0.0400
 16.08   0.946  -0.0400
 17.32   0.943  -0.0400
 19.04   0.956  -0.0400
 16.86   0.939  -0.0400
 15.27   0.943  -0.0400
 13.65   0.966  -0.0400
 12.21   1.023  -0.0400
 10.78   1.028  -0.0400
  9.40   1.007  -0.0400
  7.80   0.909  -0.0400
  6.40   0.813  -0.0400
  4.79   0.710  -0.0400
  3.26   0.575  -0.0400
  1.62   0.378  -0.0400
  0.12   0.152  -0.0400
 -1.39  -0.014  -0.0400
 -2.88  -0.113  -0.0400
 -4.34  -0.237  -0.0400
 -5.91  -0.366  -0.0400
Tabulated from data in file AB00141.DAT & reduced using program Q01.00L

Average Reynolds #:
 203100 
Number of angles of attack:
 33 
 alpha /   Cl   /  Cm
 -6.86  -0.454  -0.0400
 -2.80  -0.079  -0.0400
 -2.64  -0.067  -0.0400
 -0.74   0.149  -0.0400
  0.50   0.300  -0.0400
  2.41   0.506  -0.0400
  3.65   0.633  -0.0400
  5.50   0.776  -0.0400
  6.75   0.868  -0.0400
  8.59   0.988  -0.0400
  9.69   1.058  -0.0400
 11.33   1.105  -0.0400
 12.85   1.093  -0.0400
 14.52   1.076  -0.0400
 16.03   1.049  -0.0400
 17.49   1.044  -0.0400
 18.60   0.939  -0.0400
 16.85   1.004  -0.0400
 14.90   1.047  -0.0400
 13.75   1.094  -0.0400
 11.98   1.097  -0.0400
 10.97   1.090  -0.0400
  9.46   1.041  -0.0400
  7.98   0.941  -0.0400
  6.43   0.835  -0.0400
  4.73   0.718  -0.0400
  3.07   0.569  -0.0400
  1.90   0.445  -0.0400
  0.08   0.243  -0.0400
 -1.13   0.093  -0.0400
 -3.00  -0.110  -0.0400
 -4.21  -0.219  -0.0400
 -6.18  -0.388  -0.0400
Tabulated from data in file AB00139.DAT & reduced using program Q01.00L

Average Reynolds #:
 304000 
Number of angles of attack:
 33 
 alpha /   Cl   /  Cm
 -5.67  -0.336  -0.0400
 -4.01  -0.189  -0.0400
 -2.62  -0.037  -0.0400
 -0.86   0.171  -0.0400
  0.64   0.322  -0.0400
  2.48   0.511  -0.0400
  3.78   0.638  -0.0400
  5.76   0.792  -0.0400
  7.12   0.896  -0.0400
  8.55   0.998  -0.0400
  9.99   1.081  -0.0400
 11.28   1.105  -0.0400
 12.70   1.126  -0.0400
 13.85   1.097  -0.0400
 15.48   1.053  -0.0400
 17.07   1.066  -0.0400
 18.46   1.074  -0.0400
 16.91   1.068  -0.0400
 15.58   1.058  -0.0400
 13.76   1.112  -0.0400
 12.67   1.109  -0.0400
 10.84   1.096  -0.0400
  9.50   1.056  -0.0400
  8.04   0.958  -0.0400
  6.48   0.848  -0.0400
  4.70   0.703  -0.0400
  3.19   0.575  -0.0400
  1.26   0.378  -0.0400
  0.03   0.253  -0.0400
 -1.57   0.083  -0.0400
 -2.71  -0.056  -0.0400
 -4.51  -0.245  -0.0400
 -5.81  -0.357  -0.0400
Tabulated from data in file AB00137.DAT & reduced using program Q01.00L

File s6062.lft created on 12-05-1997 at 15:25:51 using program FORMAT