%                BOREDOM FIGHTER   
%                     DATA 
%**************************************************


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

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

    ARw = 8.0;
    ARt = 4.0;
    ARv = 0.947;

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

    bw = 20.0;
    bt = 6.25;
    bv = 1.5;


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

    Sw = 100.0;
    St = 13.44;
    Sv = 8.66;
    Sfus = 73.0 ;
% cw  ............ Wing Chord
% ct  ............ Horizontal Tail Chord
% cv  ............ Vertical Tail Chord

    cw = 2.5;
    ct = 2.375;
    cv = 3.4;

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

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


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

    wlambda = 1.0;
    hlambda = 0.65;
%    vlambda = ;

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

     Claw = 4.82;
     Clat = 3.99;
     Clav = 2.58;

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

      Er = 0.25;
      Ee = 0.30; 

% 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

      nh =  0.90;
      nv =  0.90;
      lh = 9.12;
      lv =  9.43;
      zv =  0.75;
       x =  -0.25;


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

     k1 = 1.27;
     k2 = 1.14;
     Cf = 0.008;
      e = 0.70;


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

     dsdB = 0.0;
     deda = 0.40;


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

   ClB = -0.044;



%               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
%*************************************************************



  Vt = 146.0;
  rho = 2.378e-3;
  Ix = 400.5;
  Iy = 321.600;
  Iz = 662.16;
  m = 1008/32.2;
  g = 32.2;




