XFOIL         Version 6.94
  
 Calculated polar for: Rhode St. Genese 32                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.6398   0.01312   0.00657  -0.0869  0.3077  1.0000
   0.500   0.6813   0.01363   0.00705  -0.0846  0.3083  1.0000
   1.000   0.7235   0.01424   0.00766  -0.0825  0.3083  1.0000
   1.500   0.7645   0.01525   0.00872  -0.0804  0.3047  1.0000
   2.000   0.8032   0.01659   0.01017  -0.0780  0.3012  1.0000
   2.500   0.8380   0.01832   0.01206  -0.0751  0.2981  1.0000
   4.500   1.0306   0.01560   0.00867  -0.0697  0.2907  1.0000
   5.000   1.0716   0.01531   0.00830  -0.0672  0.2879  1.0000
   5.500   1.1092   0.01511   0.00806  -0.0641  0.2837  1.0000
   6.000   1.1425   0.01508   0.00803  -0.0602  0.2768  1.0000
   6.500   1.1659   0.01520   0.00818  -0.0544  0.2664  1.0000
   7.000   1.1886   0.01551   0.00842  -0.0488  0.2399  1.0000
   7.500   1.1732   0.01714   0.00934  -0.0377  0.1714  1.0000
   8.000   1.1697   0.01896   0.01104  -0.0295  0.1302  1.0000
   8.500   1.1551   0.02195   0.01363  -0.0213  0.0721  1.0000
   9.000   1.1427   0.02541   0.01688  -0.0143  0.0485  1.0000
  10.000   1.1392   0.03219   0.02448  -0.0061  0.0274  1.0000
  10.500   1.1203   0.03766   0.03026  -0.0031  0.0243  1.0000
  11.000   1.1542   0.03864   0.03110  -0.0024  0.0216  1.0000
  11.500   1.1632   0.04218   0.03468  -0.0012  0.0192  1.0000
  12.000   1.1537   0.04820   0.04082  -0.0010  0.0177  1.0000
  12.500   1.1526   0.05329   0.04595  -0.0005  0.0161  1.0000
  13.000   1.1390   0.06046   0.05331  -0.0012  0.0152  1.0000
  13.500   1.1258   0.06760   0.06064  -0.0021  0.0145  1.0000
  14.000   1.1007   0.07667   0.06997  -0.0041  0.0142  1.0000
  14.500   1.0804   0.08502   0.07853  -0.0058  0.0138  1.0000