Airfoil: K3311
Builder: L. Kincaid
Comment: clean

Number of Reynolds #'s:
 4 

Average Reynolds #:
 61300 
Number of angles of attack:
 33 
 alpha /   Cl   /  Cm
 -5.73  -0.372  -0.0850
 -4.26  -0.292  -0.0850
 -2.71  -0.130  -0.0850
 -1.23   0.043  -0.0850
  0.57   0.265  -0.0850
  1.89   0.436  -0.0850
  3.68   0.586  -0.0850
  5.06   0.691  -0.0850
  6.77   0.845  -0.0850
  8.26   1.029  -0.0850
  9.89   1.157  -0.0850
 11.20   1.188  -0.0850
 12.67   1.197  -0.0850
 14.31   1.191  -0.0850
 15.76   1.143  -0.0850
 17.19   1.077  -0.0850
 18.75   1.013  -0.0850
 17.13   1.127  -0.0850
 15.68   1.160  -0.0850
 14.04   1.197  -0.0850
 12.55   1.201  -0.0850
 11.05   1.197  -0.0850
  9.59   1.141  -0.0850
  8.11   1.013  -0.0850
  6.59   0.851  -0.0850
  4.99   0.708  -0.0850
  3.33   0.570  -0.0850
  1.84   0.425  -0.0850
  0.46   0.255  -0.0850
 -1.22   0.030  -0.0850
 -2.76  -0.142  -0.0850
 -4.28  -0.300  -0.0850
 -5.90  -0.401  -0.0850
Tabulated from data in file JG00125.DAT & reduced using program Q01.00L

Average Reynolds #:
 101700 
Number of angles of attack:
 33 
 alpha /   Cl   /  Cm
 -5.72  -0.350  -0.0850
 -4.15  -0.163  -0.0850
 -2.64   0.037  -0.0850
 -1.20   0.184  -0.0850
  0.44   0.361  -0.0850
  2.08   0.514  -0.0850
  3.56   0.663  -0.0850
  5.19   0.820  -0.0850
  6.81   0.975  -0.0850
  8.21   1.098  -0.0850
  9.77   1.202  -0.0850
 11.19   1.207  -0.0850
 12.66   1.207  -0.0850
 14.24   1.188  -0.0850
 15.63   1.164  -0.0850
 17.08   1.046  -0.0850
 18.74   0.966  -0.0850
 17.11   1.027  -0.0850
 15.59   1.126  -0.0850
 14.12   1.203  -0.0850
 12.66   1.201  -0.0850
 11.07   1.209  -0.0850
  9.51   1.204  -0.0850
  8.06   1.088  -0.0850
  6.47   0.951  -0.0850
  4.91   0.812  -0.0850
  3.51   0.659  -0.0850
  1.93   0.500  -0.0850
  0.23   0.338  -0.0850
 -1.22   0.168  -0.0850
 -2.73   0.016  -0.0850
 -4.29  -0.188  -0.0850
 -5.96  -0.376  -0.0850
Tabulated from data in file AB00123.DAT & reduced using program Q01.00L

Average Reynolds #:
 203300 
Number of angles of attack:
 33 
 alpha /   Cl   /  Cm
 -5.80  -0.296  -0.0850
 -4.16  -0.101  -0.0850
 -2.54   0.043  -0.0850
 -1.05   0.175  -0.0850
  0.47   0.345  -0.0850
  2.14   0.525  -0.0850
  3.56   0.681  -0.0850
  5.17   0.848  -0.0850
  6.64   0.993  -0.0850
  8.17   1.130  -0.0850
  9.84   1.198  -0.0850
 11.16   1.201  -0.0850
 12.82   1.203  -0.0850
 14.29   1.193  -0.0850
 15.67   1.171  -0.0850
 17.19   1.031  -0.0850
 18.78   1.017  -0.0850
 16.88   1.056  -0.0850
 15.56   1.174  -0.0850
 14.12   1.196  -0.0850
 12.66   1.203  -0.0850
 11.01   1.203  -0.0850
  9.67   1.196  -0.0850
  7.87   1.104  -0.0850
  6.58   0.987  -0.0850
  4.72   0.799  -0.0850
  3.19   0.637  -0.0850
  1.66   0.470  -0.0850
  0.02   0.286  -0.0850
 -1.46   0.134  -0.0850
 -2.79   0.015  -0.0850
 -4.51  -0.143  -0.0850
 -5.91  -0.313  -0.0850
Tabulated from data in file AB00121.DAT & reduced using program Q01.00L

Average Reynolds #:
 304600 
Number of angles of attack:
 33 
 alpha /   Cl   /  Cm
 -5.69  -0.238  -0.0850
 -4.31  -0.114  -0.0850
 -2.76   0.027  -0.0850
 -1.02   0.187  -0.0850
  0.47   0.352  -0.0850
  2.06   0.521  -0.0850
  3.52   0.671  -0.0850
  5.16   0.836  -0.0850
  6.77   0.992  -0.0850
  8.18   1.105  -0.0850
 10.02   1.172  -0.0850
 11.41   1.182  -0.0850
 12.92   1.188  -0.0850
 14.38   1.179  -0.0850
 15.86   1.146  -0.0850
 16.88   1.092  -0.0850
 18.45   1.003  -0.0850
 17.03   1.067  -0.0850
 15.43   1.166  -0.0850
 13.95   1.183  -0.0850
 12.60   1.186  -0.0850
 11.12   1.179  -0.0850
  9.52   1.159  -0.0850
  7.90   1.080  -0.0850
  6.36   0.947  -0.0850
  4.55   0.767  -0.0850
  3.32   0.641  -0.0850
  1.71   0.474  -0.0850
  0.39   0.329  -0.0850
 -1.47   0.134  -0.0850
 -2.80   0.010  -0.0850
 -4.35  -0.127  -0.0850
 -5.81  -0.264  -0.0850
Tabulated from data in file AB00119.DAT & reduced using program Q01.00L

File k3311.lft created on 12-05-1997 at 15:25:50 using program FORMAT