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      FDC help: Airdata Group
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    <h2>
      Subsystem <i>Airdata Group</i>
    </h2>
    <p>The subsystem <i>Airdata Group</i> from the <i><a href=
    "beaver.htm">Beaver</a></i> model consists of four masked subsystem blocks: <i><a
    href="atmosph.htm">Atmosph</a></i>, <i><a href=
    "airdata1.htm">Airdata1</a></i>, <i><a href=
    "airdata2.htm">Airdata2</a></i>, and <i><a href=
    "airdata3.htm">Airdata3</a></i>. The block <i>Atmosph</i> computes a number
    of atmospheric properties, <i>Airdata1</i> computes the basic airdata
    variables, and <i>Airdata2</i> and <i>Airdata3</i> compute additional
    airdata (-related) variables.</p>
    <p> The results from the masked subsystem <i>Atmosph</i> are needed by the
    three <i>Airdata</i> blocks, and the results from <i>Airdata1</i> are
    needed by <i>Airdata2</i> and <i>Airdata3</i>. For this reason, the block
    <i>Atmosph</i> has been located on the upper left side of the subsystem,
    <i>Airdata1</i> has been located in the middle of the subsystem, and
    <i>Airdata2</i> and <i>Airdata3</i> have been located on the lower right
    side of the subsystem. The vertical shift is needed in order to be able to
    connect the outputvectors from the different blocks to the <i>Outports</i>
    on the right side of the subsystem <i>Airdata Group</i>.</p>
     <p><b>Note</b>: ICAO Standard Atmosphere is used for the atmosphere model.
    See for instance <a href="#Standard Atmosphere">ref.[1]</a> for details
    about that model. </p>
    <h3>
      Inputvector: <i>x</i>
    </h3>
<pre>
  x = [V alpha beta p q r psi theta phi xe ye H]&#39;        (states)

  V    : true 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, relative to Earth-axes [m]               }
 {ye   : Y-coordinate, relative to Earth-axes [m]               }
  H    : altitude above sea level [m]
</pre>
    <p>The curly braces denote state variables which are not needed by the masked
    subsystem blocks in the subsystem <i>Airdata Group</i>.</p> 
    <h3>
      Outputvectors: <i>yatm</i>, <i>yad1</i>, <i>yad2</i>, and <i>yad3</i>
    </h3>
<pre>
  yatm = [rho ps T mu g]&#39;                  (outputs from <a href=
"atmosph.htm">Atmosph</a>)
  yad1 = [a M qdyn]&#39;                      (outputs from <a href=
"airdata1.htm">Airdata1</a>)
  yad2 = [qc Ve Vc]&#39;                      (outputs from <a href=
"airdata2.htm">Airdata2</a>)
  yad3 = [Tt Re Rc]&#39;                      (outputs from <a href=
"airdata3.htm">Airdata3</a>)


  rho  : air density [kg/m^3]
  ps   : static pressure [N/m^2]
  T    : air temperature [K]
  mu   : dynamic viscosity [kg/(m*s)]
  g    : acceleration of gravity [m/s^2]

  a    : speed of sound [m/s]
  M    : Mach number [-]
  qdyn : dynamic pressure [N/m^2]

  qc   : impact pressure [N/m^2]
  Ve   : equivalent airspeed [m/s]
  Vc   : calibrated airspeed [m/s]

  Tt   : total temperature [K]
  Re   : Reynolds number per unit length [1/m]
  Rc   : Reynolds number with respect to mean aerodyn. chord [-]
</pre>
    <h3>
      Parameters to be defined in the Matlab workspace
    </h3>
    <ul>
      <li>
        <i>GM1</i>: vector with some important geometrical properties of the
        &#39;Beaver&#39; aircraft, and the mass of the aircraft (which is
        assumed to be constant during the motions of interest). This vector is
        needed by <i>Airdata3</i>. <i>GM1</i> can be loaded into the workspace
        from file by running the utility <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.
      </li>
    </ul>
    <h3>
      <a name="Standard Atmosphere">References</a>
    </h3>
    <ol>
      <li>
        Ruijgrok, G.J.J. <i>Elements of airplane performance</i>. Delft
        University Press, Delft, The Netherlands, 1993.
      </li>
    </ol>
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