XFOIL         Version 6.94
  
 Calculated polar for: FX 77-W-121                                     
  
 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   0.3063   0.01180   0.00339  -0.0301  0.4441  0.0521
   0.500   0.3609   0.01208   0.00362  -0.0297  0.4542  0.0390
   1.000   0.4129   0.01263   0.00434  -0.0289  0.4585  0.0581
   1.500   0.4614   0.01254   0.00394  -0.0275  0.4549  0.0293
   2.000   0.5094   0.01215   0.00329  -0.0252  0.4387  0.0262
   2.500   0.5538   0.01169   0.00314  -0.0230  0.4265  0.0475
   3.000   0.7781   0.00985   0.00320  -0.0598  0.3744  0.9773
   3.500   0.8039   0.00956   0.00267  -0.0541  0.3436  0.9299
   5.000   0.7995   0.01215   0.00373  -0.0159  0.4051  0.1086
   5.500   0.9528   0.01419   0.00594  -0.0419  0.0840  0.9847
   6.000   1.1546   0.01111   0.00517  -0.0697  0.3904  1.0000
   7.000   0.8351   0.01784   0.00739   0.0156  0.0113  0.0568
   7.500   1.1402   0.01803   0.00984  -0.0398  0.0101  1.0000
   8.000   1.3020   0.01250   0.00637  -0.0562  0.2826  1.0000
   9.500   1.0850   0.01862   0.00985   0.0170  0.1265  0.0558
  10.000   1.2058   0.02650   0.01905  -0.0157  0.0164  1.0000
  10.500   1.0175   0.03282   0.02372   0.0193  0.0092  0.2411
  11.000   1.0270   0.03740   0.02920   0.0192  0.0145  0.4823
  11.500   1.0268   0.04200   0.03349   0.0210  0.0062  0.0643