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# Common geometry data of solid and aerodynamic model (kg, m, s)
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  b     =   15;  % Span of wing
  cr    = 0.75;  % Chord length of wing at wing root
  ct    = 0.45;  % Chord length of wing at wing tip
  delta =    2;  % Dihedral angle in degrees
  lr    =  0.4;  % Aileron length ratio
  fr    =  0.2;  % Aileron flap ratio
  at    =   -2;  % Angle of incidence at wing tip (in degrees)
  l     =  6.8;  % Length of fuselage
  be    =  2.0;  % Span of elevator
  h     =  1.3;  % Height of fin
  xle   = 1.55;  % x-position of leading edge
  ds    =  1.0;  % Distance of yaw string from center of mass
