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    VT Aerospace Aircraft Design Software Series
  **************************************************

                   Program LDstab
  The program estimates Lateral/Directional Stability
  and Control derivatives for transonic tranport class
  aircraft.

  Written by Joel Grasmeyer.
  This program modified by
    - W.H. Mason, March 2000,
    - L.T. Leifsson, March 2004.

  The Department of Aerospace and Ocean Engineering,
  Virginia Tech, Blacksburg, VA 24061
  http://www.aoe.vt.edu, email: whmason@vt.edu

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    Data set title: boeing747                                                               
 
               Input Data
 
             1 = write_flag
        7.0000 = dihedral_wing
        6.2000 = z_wing
       23.0000 = dia_fuse
     5500.0000 = sref
       33.5000 = hspan_vtail
       14.4000 = depth_fuse_vtail
       36.4000 = c_vtail_root
       11.5000 = c_vtail_tip
        0.2500 = mach_eo
       45.0000 =sweep_vtail_1_4
       33.5000 = sweep_wing_1_2
       97.8000 = hspan_wing
        1.1100 = cl
       26.0000 = z_vtail
      100.0000 = l_vtail
      225.2000 = length_fuse
             4 = new
             0 = nef
        8.4000 = dia_nacelle
     1467.0000 = sh
        0.0024 = rho_eo
     1116.4000 = a_eo
    0.3737E-06 = mu_eo
       15.0000 = dr_max
        0.0000 = xbar
       27.3100 = cbar
 
            Output Results

   stability derivatives

                          -0.0401 = cy_beta_wing
                          -0.2941 = cy_beta_fuse
                          -0.3482 = cy_beta_vtail
 
       -0.9601 = cy_beta (adjusted)
 
                          -0.2763 = cl_beta_wingbody
                           0.0000 = cl_beta_htail
                          -0.0284 = cl_beta_vtail
 
       -0.2210 = cl_beta (adjusted)
 
                           0.0500 = cn_beta_wing
                          -0.1263 = cn_beta_fuse
                           0.1817 = cn_beta_vtail
 
        0.1500 = cn_beta (adjusted)

   control derivatives

        0.0000 = cy_da
        0.0461 = cl_da
        0.0064 = cn_da
 
       -0.1750 = cy_dr
       -0.0070 = cl_dr
        0.1090 = cn_dr

   engine out information - 5 deg bank and max rudder

        3.0396 = beta (deg)
        5.0000 = phi (deg)
       16.8301 = da (deg)
       15.0000 = dr (deg)
        2.3776 = ar_vtail_eff
        0.0384 = cn_avail

   Calculations completed