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      FDC help: Aeromod (Beaver)
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    <h2>
      Subsystem <i>Aeromod (Beaver)</i>
    </h2>
    <p><i>Aeromod (Beaver)</i> determines the
    aerodynamic force and moment coefficients for the DHC-2 &#39;Beaver&#39;.
    The aerodynamic model is aircraft-dependent, hence, this block must be
    replaced if models of other aircraft are to be implemented in the
    simulation structure of FDC.</p>
    
    <p>Instant replacement of the block <i>Aeromod
    (Beaver)</i> is possible only if the same inputs and outputs to and from
    this block remain the same. However, the internal structure of a
    replacement for the current block <i>Aeromod</i> may look completely
    different. For instance, the aerodynamic model of the DHC-2
    &#39;Beaver&#39;, contained in <i>Aeromod (Beaver)</i> determines the force
    and moment coefficients by means of evaluation of six polynomial equations
    (<a href="#References">see ref.[1]</a>), whereas it is more customary to
    compute aerodynamic forces and moments by means of interpolation in large
    multi-dimensional tables.</p>
    
    <p>The block <i>Aeromod</i> is contained in the
    subsystem <i><a href="aerogrp.htm">Aerodynamics Group (Beaver)</a></i> of
    the <i><a href="beaver.htm">Beaver</a></i> model. Other blocks within that
    subsystem are: <i><a href="dimless.htm">Dimless</a></i>, and <i><a href=
    "fmdims.htm">FMdims</a></i>.</p>
     <p><b>Note:</b> The side-force coefficient with respect to beta-dot has been
    neglected in the block <i>Aeromod (Beaver)</i>, because it would have
    yielded an algebraic loop. Therefore, the beta-dot equation has been
    written out as an explicit equation with an aircraft-independent and an
    aircraft-dependent term. The latter is evaluated in a separate block <i><a
    href="xdotcorr.htm">xdotcorr (Beaver)</a></i>, which is contained in the
    subsystem <i><a href="eqmotion.htm">Aircraft Equations of Motion</a></i>. </p>
    <h3>
      Inputvectors: <i>x</i>, <i>uaero</i>, <i>ydl</i>
    </h3>
<pre>
  x    = [V alpha beta p q r psi theta phi xe ye H]&#39;     (states)
  uaero= [deltae deltaa deltar deltaf]&#39;      (aerodynamic inputs)
  ydl  = [pb/2V qc/V rb/2V]&#39;           (dimensionless velocities,
                                   computed in the block <a href=
"dimless.htm">Dimless</a>)

 {V    : airspeed [m/s]                                         }
  alpha: angle of attack [rad]
  beta : sideslip angle [rad]
 {p    : roll rate [rad/s]                                      }
 {q    : pitch rate [rad/s]                                     }
 {r    : yaw rate [rad/s]                                       }
 {psi  : yaw angle [rad]                                        }
 {theta: pitch angle [rad]                                      }
 {phi  : roll angle [rad]                                       }
 {xe   : x-coordinate in Earth-fixed reference frame [m]        }
 {ye   : y-coordinate &#39;&#39;     &#39;&#39;          &#39;&#39;      &#39;&#39;  [m]        }
 {H    : altitude above sea-level [m]                           }

  deltae: elevator deflection [rad]
  deltaa: deflection of the ailerons [rad]
  deltar: rudder deflection [rad]
  deltaf: flap setting [rad]

  pb/2V: dimensionless roll rate [-]
  qc/V : dimensionless pitch rate [-]
  rb/2V: dimensionless yaw rate [-]
</pre>
    <p>The inputvariables which are not actually used by <i>Aeromod (Beaver)</i>
    have been displayed between curly braces.</p> 
    <h3>
      Outputvector: <i>Caero</i>
    </h3>
<pre>
  Caero = [CXa CYz CZa Cla Cma Cna]&#39;

  CXa, CYa, CZa: dimensionless aerodynamic force coefficients
  Cla, Cma, Cna: dimensionless aerodynamic moment coefficients.
</pre>
    <h3>
      Parameters, which must be defined in the Matlab Workspace
    </h3>
    <ul>
      <li>
        <i>AM</i>: matrix with stability and control derivatives of the
        &#39;Beaver&#39; (valid only for the nonlinear aerodynamic model of the
        DHC-2 &#39;Beaver&#39;, see <a href="#References">ref.[1]</a>). The
        matrix <i>AM</i> can be loaded into the Matlab workspace from file by
        running <i><a href="datload.htm">DATLOAD</a></i>. Run <i><a
        href="modbuild.htm">MODBUILD</a></i> first if this datafile
        does not yet exist.
      </li>
    </ul>
    <h3>
      <a name="References">References</a>
    </h3>
    <ol>
      <li>
        R.T.H. Tjee and J.A. Mulder. <i>Stability and Control Derivatives of
        the De Havilland DHC-2 &quot;Beaver&quot; aircraft</i>. Report LR-556,
        Delft University of Technology, 1988.
      </li>
    </ol>
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