%                   M P X - 5    
%                     DATA 
%**************************************************

% To access this data in MATLAB type the file name in the MATLAB
% environment.





%                    GEOMETRY
%**************************************************

% ARw ............ Wing Aspect Ratio
% ARt ............ H-Tail Aspect Ratio
% ARv ............ V-Tail Aspect Ratio

    ARw = 6.0;
    ARt = 4.17;
    ARv = 2.95;

% bw  ............ Wing Span
% bt  ............ H-Tail Span
% bv  ............ V-Tail Span

    bw = 90/12;
    bt = 32/12;
    bv = 14.5/12;


% Sw  ............ Wing Area
% St  ............ Horizontal Tail Area
% Sv  ............ Vertical Tail Area
% Sfus ........... Fuselage wetted area

    Sw = 1350/144;
    St = 245/144;
    Sv = 143/144;
    Sfus = 1067/144;
% cw  ............ Wing Chord
% ct  ............ Horizontal Tail Chord
% cv  ............ Vertical Tail Chord

    cw = 15.0/12;
    ct = 8/12;
    cv = 9/12; 

% ws ............. Wing Sweep Angle
% wt ............. Horizontal Tail Sweep Angle
% wv ............. Vertical Tail Sweep Angle

    ws = 0.0;
    ts = 16.0;
    vs = 0.0;


% wlambda ........ Taper Ratio for wing 
% tlambda ........ Taper ratio for horizontal tail 
% vlambda ........ Taper ratio for vertical tail

    wlambda = 1.0;
    hlambda = 0.6;
    vlambda = 6.5/12;

% Claw ........... 3-D  Wing lift curve slope
% Clat ........... 3-D  Horizontal tail slope
% Clav ........... 3-D  Vertical Tail Lift curve slope

     Claw = 4.39;
     Clat = 3.72;
     Clav = 3.16;

% Er.............. Rudder Flap to Chord ratio
% Ee.............. Elevator Flap to Chord ratio

      Er = 0.3556;
      Ee = 0.266;

% nh............. Horizontal Tail Efficiency
% nv ............ Vertical Tail Efficiency
% lh ............ Distance from c.g. to horizontal tail A.C. 
% lv ............ Distance from c.g. to vertical tail A.C.
% zv ............ Vertical distance from v-tail C.P. to c.g.
%  x............. distance between wing ac and c.g.
%                 Aft of c.g. is positive
       x =  0.41;
      nh =  1.0;
      nv =  1.0;
      lh =  (41.93-x)/12;
      lv =  (41.66-x)/12; 
      zv =  7/12;
       x = 0.41/12;

%  k1............ correction factor for wing thickness
%  k2............ fuselage fineness ratio correction factor
%  Cf............ Skin Friction Coefficient
%  e ............ Oswald's efficiency 

     k1 = 1.26;
     k2 = 1.12;
     Cf = 0.006;
      e = 0.85;


 
% dsdB........... Change in sidewash angle with Beta Change
% deda........... Change is downwash with alpha 

     dsdB = 0.0;
     deda = 0.37;

% ClB .................Roll Moment derivative wrt Beta

   ClB = -0.0147;


%               OTHER VARIABLES
%*********************************************
% Vt ................. Trim velocity ft/sec
% rho ................ Density slug/ft3
% Ix ................. X Moment of Inertia  slug.ft2
% Iy ................. Y Moment of Inertia  slug.ft2
% Iz ................. Z Moment of Inertia  slug.ft2
% m .................. Aircraft Mass  slug
% g .................. Gravitational acceleration
%*************************************************************


  % The trim velocity is determined from the velocity vector of 
  % the time history.  
  Vt = mean(v);
  rho = 2.3e-3;
  Ix = .769;
  Iy = 1.10;
  Iz = 1.84;
  m = 0.598;
  g = 32.2;




