1 2 3 4 5 6 7 8 9 10 11 ---------------------------------------------------------------
 Vortex Lattice Output -- Total Forces

 Configuration: Baseline                                                    
     # Surfaces =   5
     # Strips   =  58
     # Vortices = 406

  Sref =  1901.0       Cref =  20.601       Bref =  94.488    
  Xref =  47.992       Yref =  0.0000       Zref =  12.780    

 Standard axis orientation,  X fwd, Z down         

 Run case: LiftOff                                 

  Alpha =   0.00000     pb/2V =   0.00000     p'b/2V =   0.00000
  Beta  =   0.00000     qc/2V =   0.00000
  Mach  =     0.000     rb/2V =   0.00000     r'b/2V =   0.00000

  CXtot =  -0.06880     Cltot =   0.00000     Cl'tot =   0.00000
  CYtot =   0.00000     Cmtot =   0.06121
  CZtot =  -0.71702     Cntot =   0.00000     Cn'tot =   0.00000

  CLtot =   0.71702
  CDtot =   0.06880
  CDvis =   0.02700     CDind =   0.04180
  CLff  =   0.71100     CDff  =   0.05034    | Trefftz
  CYff  =   0.00000         e =    0.6806    | Plane  
 
   Aileron         =   0.00000
   Elevator        =   0.00000
   Rudder          =   0.00000
 
 ---------------------------------------------------------------

 Derivatives...
                             alpha                beta
                  ----------------    ----------------
 z force     |    CLa =   4.172359    CLb =   0.000000
 y force     |    CYa =   0.000000    CYb =  -0.264661
 roll  x mom.|    Cla =   0.000000    Clb =  -0.083353
 pitch y mom.|    Cma =  -0.387042    Cmb =   0.000000
 yaw   z mom.|    Cna =   0.000000    Cnb =   0.116272

                      roll rate  p       pitch rate  q         yaw rate  r
                  ----------------    ----------------    ----------------
 z force     |    CLp =   0.000000    CLq =   5.138735    CLr =   0.000000
 y force     |    CYp =  -0.079428    CYq =   0.000000    CYr =   0.355220
 roll  x mom.|    Clp =  -0.384410    Clq =   0.000000    Clr =   0.219007
 pitch y mom.|    Cmp =   0.000000    Cmq =  -6.748740    Cmr =   0.000000
 yaw   z mom.|    Cnp =  -0.026530    Cnq =   0.000000    Cnr =  -0.187101

                  Aileron      d1     Elevator     d2     Rudder       d3 
                  ----------------    ----------------    ----------------
 z force     |   CLd1 =   0.000000   CLd2 =   0.005872   CLd3 =   0.000000
 y force     |   CYd1 =  -0.002086   CYd2 =   0.000000   CYd3 =  -0.003509
 roll  x mom.|   Cld1 =  -0.007095   Cld2 =   0.000000   Cld3 =  -0.000449
 pitch y mom.|   Cmd1 =   0.000000   Cmd2 =  -0.016896   Cmd3 =   0.000000
 yaw   z mom.|   Cnd1 =  -0.000659   Cnd2 =   0.000000   Cnd3 =   0.002143
 Trefftz drag| CDffd1 =   0.000000 CDffd2 =  -0.000847 CDffd3 =   0.000000
 span eff.   |    ed1 =   0.000000    ed2 =   0.022682    ed3 =   0.000000
 
 

 Neutral point  Xnp =  49.903019

 Clb Cnr / Clr Cnb  =   0.612440    (  > 1 if spirally stable )
