    ======================================================
    = 1903 Wright Flyer                                  =
    = for FlightGear with LaRCsim and the UIUC Aeromodel =
    =                                                    =
    = Flight model by:                                   =
    = Michael Selig, et al  (m-selig@uiuc.edu)           =
    = http://www.aae.uiuc.edu/m-selig/apasim.html     =
    =                                                    =
    = Visual model by:                                   =
    = Jim Wilson (jimw@kelcomaine.com)                   =
    = and some help from Paul Beardsley                  =
    ======================================================

    To run, try:

    fgfs --aircraft=wrightFlyer1903-v1-nl-uiuc

    Files and directory structure required in $FG_ROOT/Aircraft/ to fly the
    model:

    wrightFlyer1903-v1-nl-uiuc-set.xml
    wrightFlyer1903/Sounds/uiuc/wrightFlyer1903-sound.xml
    UIUC/wrightFlyer1903-v1-nl/aircraft.dat
    UIUC/wrightFlyer1903-v1-nl/CDfa.dat
    UIUC/wrightFlyer1903-v1-nl/Cmfa2.dat
    UIUC/wrightFlyer1903-v1-nl/Cmfade6.dat
    UIUC/wrightFlyer1903-v1-nl/CLfade.dat
    wrightFlyer1903/Models/[visual model files]

    These files above come with the FlightGear base package.

    ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~

    Model description and updates:

    12/21/02 - Updates to aircraft aero file, and tweaks (above and below)
               in this file.

    5/26/02 - First release: v1-nl

    * This model is based partly on wind tunnel tests of a 1903 Wright
      Flyer replica tested at NASA Ames by a group lead by Prof Culick at
      Caltech.  The model is a nonlinear model, meaning that stall of both
      the canard and biplane wing is included.  Because the replica was
      not tested to stall, data in this regime had to be deduced from a
      number of different sources, including low Reynolds number airfoil
      data taken at UIUC.

    * Wonder what it was like to fly the 1903 Wright Flyer?  Be a test
      pilot.  See the longitudinal static instability.  Fly steady,
      straight and level, then put in a brief canard pulse (elevator
      stick) so as not to change the trim speed.  With an up canard pulse
      and hands off the stick, the Wright Flyer will start to pitch
      upwards until it stalls.  Down pulse, and it goes down.  This same
      instability is seen by simply trying to fly straight and level!  The
      rates are low enough that a good pilot with practice can stay ahead
      of the static instability.  Stall can get pretty nasty if both the
      canard and biplane wing stall at the same time. Typically, however,
      the canard will stall first.  Full up elevator can be used to fly
      out of the dive.  But in this condition the canard is
      stalled.  Relieving the back pressure will move the canard out of
      stall and the pull-out will be a little bit faster, but the
      difference is hard to notice.  Keep in mind that this aircraft was
      flown four times before it was damaged on Dec 17, 1903.  The first
      flight was 120 feet in 12 seconds, and the last was 852 feet in 59
      seconds.  How far can you fly?

    * Run with the FGFS "enable-auto-coordination" option (default setup
      includes this option) to model the coupling between the wing warping
      and rudder to counteract the adverse yaw effect of the wing warping.
      The amount of coupling has been set to match that on the original
      Wright Flyer (see the aircraft.dat file for some specs).  The
      resulting handling is "not that great."  For later designs, the
      Wright Brothers decoupled the warping and rudder to have more
      control and the ability to fly in coordinated flight with
      cross-controls.

    * Finally, it's a hand full!

    * References:

      - Culick, F.E.C. and Jex, H.R., "Aerodynamics, Stability and
        Control of the 1903 Wright Flyer," Proceedings of The Wright
        Flyer: An Engineering Perspective, National Air and Space Museum,
        Smithsonian Institution, 1985.

      - Jex, H.R. and Culick, F.E.C., "Flight Control Dynamics of the
        1903 Wright Flyer," 12th AIAA Atmospheric Flight Mechanics
        Conference, AIAA Paper 85-1804-CP, 1985.

      - Jex, H, Grimm, R., Latz, J.P., and Hange, C., "Full-Scale 1903
        Wright Flyer Wind Tunnel Test Results From the NASA Ames Research
        Center", AIAA 38th Aerospace Sciences Meeting, AIAA Paper
        2000-0512, 2000.

      - Various other sources including
        http://www.wrightflyer.org/Papers/papers.html
        http://www.aae.uiuc.edu/m-selig/uiuc_lsat.html (low Re data)

    ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~

    **************************************************
     Prof. Michael S. Selig
     Dept. of Aerospace Engineering
     University of Illinois at Urbana-Champaign
     306 Talbot Laboratory
     104 South Wright Street
     Urbana, IL 61801-2935
     (217) 244-5757 (o), (509) 691-1373 (fax)
     m-selig@uiuc.edu
     http://www.aae.uiuc.edu/m-selig
    **************************************************