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      FDC help: Engmod (Beaver)
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    <h2>
      Subsystem <i>Engmod (Beaver)</i>
    </h2>
    <p><i>Engmod (Beaver)</i> computes the
    dimensionless force and moment coefficients due to operation of the
    powerplant, using the engine forces &amp; moments model of the DHC-2
    &#39;Beaver&#39; aircraft from <a href="#References">ref.[1]</a>.
    The block is contained in the subsystem <i><a href="enggrp.htm">Engine
    Group</a></i> of the <i><a href="beaver.htm">Beaver</a></i> model. It uses
    the outputs from the block <i><a href="power.htm">Power (Beaver)</a></i>
    and its outputs are sent to the block <i><a href=
    "fmdims.htm">FMdims</a></i>, which are both also contained in the subsystem
    <i>Engine Group</i>.</p> 
    <h3>
      Inputvectors: <i>x</i> and <i>ypow</i>
    </h3>
<pre>
  x    = [V alpha beta p q r psi theta phi xe ye H]&#39;     (states)

  ypow = [dpt P]&#39;    (dimensionless pressure increase across the
                       propeller and engine power, both computed
                                     in the block <a href=
"power.htm">Power (Beaver)</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]                           }

  dpt  : dimensionless pressure increase across the propeller [-]
 {P    : engine power [Nm/s]                                    }
</pre>
    <p>The input variables which are not actually used by <i>Engmod (Beaver)</i>
    have been displayed between curly braces.</p> 
    <h3>
      Outputvector: <i>Cprop</i> (<i>prop</i> = &#39;propulsion&#39;)
    </h3>
<pre>
  Cprop = [CXp CYp CZp Clp Cmp Cnp]&#39;

  CXp, CYp, CZp: force coefficients due to engine operation [-]
  Clp, Cmp, Cnp: moment coefficients due to engine operation [-]
</pre>
    <h3>
      Parameters to be defined in the Matlab Workspace.
    </h3>
    <ul>
      <li>
        <p><i>EM</i>: matrix with stability and control derivatives of the
        &#39;Beaver&#39; that take into account the engine operation (including slipstream effects of the propeller. The matrix <i>EM</i> can be loaded into the
        workspace from file by running the routine <i><a href=
        "datload.htm">DATLOAD</a></i>. Run <i><a href=
        "modbuild.htm">MODBUILD</a></i> first if the datafile does not yet
        exist.</p>
      </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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