************************************************
*                                              * 
*  FGFS Reconfigurable Aircraft Flight Model   *
*  Input File Documentation                    * 
*  Version 0.73, June 27, 2000                 *
*                                              *
*  Authors:                                    *
*  Jeff Scott (jscott@mail.com)                *
*  Bipin Sehgal (bsehgal@uiuc.edu)             *
*  Michael Selig (m-selig@uiuc.edu)            *
*  Dept of Aero and Astro Engineering          *
*  University of Illinois at Urbana-Champaign  *
*  Urbana, IL                                  *
*  http://amber.aae.uiuc.edu/~m-selig          *
*                                              *
************************************************ 


**********************************************************************
NOTE:  Most of the commands discussed in this documentation are 
       currently implemented in the UIUC aerodynamics model.  Those 
       denoted by '|' are proposed and will likely be added in the 
       future but are not currently implemented.  Some commands are 
       in use but not producing the desired results.  These are 
       clearly noted, so please do not attempt to use them at this 
       time.
**********************************************************************

**********************************************************************
This documentation includes:
 - Required and optional input lines.
 - Input line formats and conventions.

  Viewing this file in emacs makefile-mode with color makes this file
  easier to read.
**********************************************************************

**********************************************************************
I. Conventions and Notations and Reading this Document:

 # ...     Comments
 |         Input line not yet implemented
 |         Optional data
 |         Sometimes indicates a feature not yet used,
           but proposed convention is indicated nevertheless.
 <...>     Value or file name to be placed here
 ||        Input line disabled
 ||        Option disabled
 ...       Repeat similar data
 ->        Continue onto next line
**********************************************************************

**********************************************************************
II. General Input Line Format:

Examples input lines include

Cm Cmo           0.194  # []          Bray pg 33
Cm Cm_a         -2.12   # [/rad]      Bray pg 33
CL CLfa CLfa.dat 0 1    # []          Bray pg 50, Table 4.7

These follow the more general input line form

keyword  variableName  <value -or- file> | ->
    <value -or- file>  # [units]  <data source>

Each term of the input line will be discussed in turn.

(1) KEYWORDS
============

There currently exist the following variable keyword types:

init            Initial values for equation of motion
geometry        Aircraft-specific geometric quantities
controlSurface  Control surface deflections and properties
|controlsMixer  Control surface mixer options
mass            Aircraft-specific mass properties
engine          Propulsion data
CD              Aerodynamic x-force quantities (longitudinal)
CL              Aerodynamic z-force quantities (longitudinal)
Cm              Aerodynamic m-moment quantities (longitudinal)
CY              Aerodynamic y-force quantities (lateral)
Cl              Aerodynamic l-moment quantities (lateral)
Cn              Aerodynamic n-moment quantities (lateral)
|gear           Landing gear model quantities
ice             Icing model parameters
record          Record desired quantites to file
misc            Miscellaneous inputs

As each line of the input file is read, the code recognizes the
keyword, enters the appropriate switch statement in the code, and
proceeds to read the next term in the input line.

(2) VARIABLE NAMES
==================

The variable name indicates the form of the variable itself.  This
form may be a constant, a stability derivative (a specific form of a
constant), or a variable-dimensional lookup table.  More variable
types can be easily prescribed by defining a new convention.  The
variable name may also indicate that the quantity is to be calculated
from a hard-coded equation or set of equations provided at an
appropriate location within the code.

If the parameter name denotes a constant, a numerical value will 
follow the variable name.  If a lookup table, the name of the table 
containing the data will follow.

More than one value or file name can be specified if the code is 
intended to read in multiple pieces of data when implementing the 
particular switch in question (see also OPTIONAL data, section (3)).

The conventions used for naming the variables are provided below.
Several of these variable names are not currently used.

1) variable class
_                   denotes stability derivative
f                   "function of" (indicates data table)

2) timing data (global simulator variables)
Simtime             current simulator time                  [s]
dt                  current simulator time step             [s]

3) aircraft position data
Lat_geocentric      geocentric latitude of CG               [rad]
Lon_geocentric      geocentric longitude of CG              [rad]
Radius_to_vehicle   distance of CG from inertial frame      [ft]
Latitude            geodetic latitude of CG                 [rad]
Longitude           geodetic longitude of CG                [rad]
Altitude            height of CG above reference ellipsoid  [ft]
Phi                 Euler bank/roll angle                   [rad]
Theta               Euler pitch attitude angle              [rad]
Psi                 Euler heading angle                     [rad]

4) aircraft accelerations
V_dot_north         local x-acceleration                    [ft/s^2]
V_dot_east          local y-acceleration                    [ft/s^2]
V_dot_down          local z-acceleration                    [ft/s^2]
U_dot_body          body x-acceleration                     [ft/s^2]
V_dot_body          body y-acceleration                     [ft/s^2]
W_dot_body          body z-acceleration                     [ft/s^2]
A_X_pilot           pilot x-acceleration                    [ft/s^2]
A_Y_pilot           pilot y-acceleration                    [ft/s^2]
A_Z_pilot           pilot z-acceleration                    [ft/s^2]
A_X_cg              center of gravity x-acceleration        [ft/s^2]
A_Y_cg              center of gravity x-acceleration        [ft/s^2]
A_Z_cg              center of gravity x-acceleration        [ft/s^2]
N_X_pilot           pilot x-acceleration                    [ft/s^2]
N_Y_pilot           pilot y-acceleration                    [ft/s^2]
N_Z_pilot           pilot z-acceleration                    [ft/s^2]
N_X_cg              center of gravity x-acceleration        [ft/s^2]
N_Y_cg              center of gravity Y-acceleration        [ft/s^2]
N_Z_cg              center of gravity Z-acceleration        [ft/s^2]
P_dot_body          roll rate acceleration                  [rad/s^2]
Q_dot_body          pitch rate acceleration                 [rad/s^2]
R_dot_body          yaw rate acceleration                   [rad/s^2]

5) aircraft velocities
V_north             local x-velocity                        [ft/s]
V_east              local y-velocity                        [ft/s]
V_down              local z-velocity                        [ft/s]
V_north_rel_ground  local x-velocity with respect to ground [ft/s]
V_east_rel_ground   local y-velocity with respect to ground [ft/s]
V_down_rel_ground   local z-velocity with respect to ground [ft/s]
V_north_airmass     local x-velocity of steady airmass      [ft/s]
V_east_airmass      local y-velocity of steady airmass      [ft/s]
V_down_airmass      local z-velocity of steady airmass      [ft/s]
V_north_rel_airmass local x-velocity wrt steady airmass     [ft/s]
V_east_rel_airmass  local y-velocity wrt steady airmass     [ft/s]
V_down_rel_airmass  local z-velocity wrt steady airmass     [ft/s]
U_gust              local linear turbulence x-velocity      [ft/s]
V_gust              local linear turbulence y-velocity      [ft/s]
W_gust              local linear turbulence z-velocity      [ft/s]
U_body              wind x-velocity in body axis            [ft/s]
V_body              wind y-velocity in body axis            [ft/s]
W_body              wind z-velocity in body axis            [ft/s]
V_rel_wind          total wind velocity (freestream)        [ft/s]
V_true_kts          true velocity                           [kts]
V_rel_ground        total velocity wrt ground               [ft/s]
V_inertial          total inertial velocity                 [ft/s]
V_ground_speed      velocity at right angles to local vertical [ft/s]
V_equiv             equivalent airspeed                     [ft/s]
V_equiv_kts         equivalent airspeed                     [kts]
V_calibrated        calibrated indicated airspeed           [ft/s]
V_calibrated_kts    calibrated indicated airspeed           [kts]
P_local             local roll rate                         [rad/s]
Q_local             local pitch rate                        [rad/s]
R_local             local yaw rate                          [rad/s]
P_body              body roll rate                          [rad/s]
Q_body              body pitch rate                         [rad/s]
R_body              body yaw rate                           [rad/s]
P_total             roll rate of body axis wrt local axis   [rad/s]
Q_total             pitch rate of body axis wrt local axis  [rad/s]
R_total             yaw rate of body axis wrt local axis    [rad/s]
Phi_dot             change in bank angle rate               [rad/s]
Theta_dot           change in pitch attitude angle rate     [rad/s]
Psi_dot             change in heading angle rate            [rad/s]
Latitude_dot        change in geocentric latitude rate      [rad/s]
Longitude_dot       change in geocentric longitude rate     [rad/s]
Radius_dot          change in geocentric radius rate        [ft/s]

6) angles
Alpha               angle of attack                         [rad]
Alpha_deg           angle of attack                         [deg]
Alpha_dot           rate of change of alpha                 [rad/s]
Alpha_dot_deg       rate of change of alpha                 [deg/s]
Beta                sideslip angle                          [rad]
Beta_deg            sideslip angle                          [deg]
Beta_dot            rate of change of beta                  [rad]
Beta_dot_deg        rate of change of beta                  [deg]
Gamma_vert          local vertical flight path angle        [rad]
Gamma_ver_deg       local vertical flight path angle        [deg]
Gamma_horiz         local horizontal flight path angle      [rad]
Gamma_horiz_deg     local horizontal flight path angle      [deg]

7) atmosperic properties
Density             atmospheric density                     [slug/ft^3]
V_sound             speed of sound                          [ft/s]
Mach_number         free-stream Mach number                 []
M                   Mach number                             []
Re                  Reynolds number                         []
Static_pressure     static pressure                         [lb/ft^2]
Total_pressure      total pressure                          [lb/ft^2]
Impact_pressure     impact pressure                         [lb/ft^2]
Dynamic_pressure    dynamic pressure                        [lb/ft^2]
Static_temperature  static temperature                      [deg F?]
Total_temperature   total temperature                       [deg F?]

8) Earth properties
Gravity             acceleration due to gravity             [ft/s^2]
Sea_level_radius    local Earth radius                      [ft]
Earth_position_angle Earth rotation angle since reference time [rad]
Runway_altitude     runway height above local sea level     [ft]
Runway_latitude     runway latitude                         [rad]
Runway_longitude    runway longitude                        [rad]
Runway_heading      runway heading                          [rad]
Radius_to_rwy       geocentric radius to runway             [ft]
D_pilot_north_of_rwy  local pilot x-distance from runway    [ft]
D_pilot_east_of_rwy   local pilot y-distance from runway    [ft]
D_pilot_down_of_rwy   local pilot z-distance from runway    [ft]
X_pilot_rwy         pilot x-distance from rwy in rwy axis   [ft]
Y_pilot_rwy         pilot y-distance from rwy in rwy axis   [ft]
H_pilot_rwy         pilot z-distance from rwy in rwy axis   [ft]
D_cg_north_of_rwy   local cg x-distance from runway         [ft]
D_cg_east_of_rwy    local cg y-distance from runway         [ft]
D_cg_down_of_rwy    local cg z-distance from runway         [ft]
X_cg_rwy            cg x-distance from rwy in rwy axis      [ft]
Y_cg_rwy            cg y-distance from rwy in rwy axis      [ft]
H_cg_rwy            cg z-distance from rwy in rwy axis      [ft]

9) aircraft geometric variables
bw        wingspan                              [ft]
cbar      mean aerodynamic chord                [ft]
Sw        wing planform area                    [ft^2]
|iw       wing incidence angle                  [deg]
|bc       canard span                           [ft]
|cc       canard (mean) chord                   [ft]
|Sc       canard area                           [ft^2]
|ic       canard incidence angle                [deg]
bh        horizontal tail span                  [ft]
ch        horizontal tail (mean) chord          [ft]
Sh        horizontal tail area                  [ft^2]
ih        horizontal tail incidence angle       [deg]
|bv       vertical tail span (height)           [ft]
|cv       vertical tail (mean) chord            [ft]
|iv       vertical tail incidence angle         [deg]
|Sv       vertical tail area                    [ft^2]
Dx_pilot  reference pilot x-location            [ft]
Dy_pilot  reference pilot y-location            [ft]
Dz_pilot  referende pilot z-location            [ft]
Dx_cg     reference center of gravity x-loc     [ft]
Dy_cg     reference center of gravity y-loc     [ft]
Dz_cg     reference center of gravity z-loc     [ft]

10) aircraft control surface properties
|Sa            aileron area                     [ft^2]
|Se            elevator area                    [ft^2]
|Sf            flap area                        [ft^2]
|Sr            rudder area                      [ft^2]
Long_control   pitch control input              []
Long_trim      longitudinal trim input          [rad]
set_Long_trim  set longitudinal trim to constant[rad]
zero_Long_trim set longitudinal trim to zero    [deg]
elevator       elevator deflection              [rad]
Lat_control    roll control input               []
aileron        aileron deflection               [rad]
Rudder_pedal   yaw control input                []
rudder         rudder deflection                [rad]
|flap          flap deflection                  [rad]

11) user-specified control surface deflections
elevator_step_angle        elevator step input angle            [deg]
elevator_step_startTime    elevator step input starting time    [s]
elevator_singlet_angle     elevator singlet input angle         [deg]
elevator_singlet_startTime elevator singlet input starting time [s]
elevator_singlet_duration  elevator singlet time duration       [s]
elevator_doublet_angle     elevator singlet input angle         [deg]
elevator_doublet_startTime elevator doublet input starting time [s]
elevator_doublet_duration  elevator doublet TOTAL time duration [s]
elevator_input_file        file of elevator deflections vs. time [s,deg]

12) mass variables
Weight              gross takeoff weight                    [lb]
Mass                aircraft mass (used by LaRCsim)         [slug]
I_xx                roll inertia                            [slug-ft^2]
I_yy                pitch inertia                           [slug-ft^2]
I_zz                yaw inertia                             [slug-ft^2]
I_xz                lateral cross inertia                   [slug-ft^2]

13) engine/propulsion variables
|thrust             engine thrust                           [lb]
simpleSingle        treat all engines as one; max thrust    [lb]
Throttle_pct        throttle input ("stick")                []
Throttle_3          throttle deflection (determines thrust) [%]

14) force/moment coefficients
CD                  coefficient of drag                     []
CY                  coefficient of side-force               []
CL                  coefficient of lift                     []
Cl                  coefficient of roll moment              []
Cm                  coefficient of pitching moment          []
Cn                  coefficient of yaw moment               []
|CT                 coefficient of thrust                   []

15) total forces/moments
F_X_wind            aerodynamic x-force in wind-axes        [lb]
F_Y_wind            aerodynamic y-force in wind-axes        [lb]
F_Z_wind            aerodynamic z-force in wind-axes        [lb]
F_X_aero            aerodynamic x-force in body-axes        [lb]
F_Y_aero            aerodynamic y-force in body-axes        [lb]
F_Z_aero            aerodynamic z-force in body-axes        [lb]
F_X_engine          propulsion x-force in body axes         [lb]
F_Y_engine          propulsion y-force in body axes         [lb]
F_Z_engine          propulsion z-force in body axes         [lb]
F_X_gear            gear x-force in body axes               [lb]
F_Y_gear            gear y-force in body axes               [lb]
F_Z_gear            gear z-force in body axes               [lb]
F_X                 total x-force in body-axes              [lb]
F_Y                 total y-force in body-axes              [lb]
F_Z                 total z-force in body-axes              [lb]
F_north             total x-force in local-axes             [lb]
F_east              total y-force in local-axes             [lb]
F_down              total z-force in local-axes             [lb]
M_l_aero            aero roll-moment in body-axes           [ft-lb]
M_m_aero            aero pitch-moment in body-axes          [ft-lb]
M_n_aero            aero yaw-moment in body-axes            [ft-lb]
M_l_engine          prop roll-moment in body axes           [ft-lb]
M_m_engine          prop pitch-moment in body axes          [ft-lb]
M_n_engine          prop yaw-moment in body axes            [ft-lb]
M_l_gear            gear roll-moment in body axes           [ft-lb]
M_m_gear            gear pitch-moment in body axes          [ft-lb]
M_n_gear            gear yaw-moment in body axes            [ft-lb]
M_l_rp              total roll-moment                       [ft-lb]
M_m_rp              total pitch-moment                      [ft-lb]
M_n_rp              total yaw-moment                        [ft-lb]

16) landing gear properties
|cgear              gear damping constant                   [?]
|kgear              gear spring constant                    [?]
|muGear             gear rolling friction coef              [?]
|strutLength        gear strut length                       [ft]

17) icing model parameters
iceTime       time when icing begins                         [s]
transientTime time period over which eta increases to final  [s]
eta_ice_final icing severity factor at end of transient time []
kCA           icing constants for associated aero coef.      [] (see IV)
beta_probe_wing  location of flow angle probe on wing        [ft]
beta_probe_tail  location of flow angle probe on tail        [ft]

18) subscripts
o       value for all angles = 0 (alfa, beta, etc)
a       angle of attack
a2      alpha squared
a3      alpha cubed
adot    rate change in angle alpha
beta    sideslip angle
b2      beta squared
b3      beta cubed
bdot    rate change in beta
p       roll rate
q       pitch rate
r       yaw rate
|pdot   rate change in p
|qdot   rate change in q
|rdot   rate change in r
|udot   rate change in x-velocity
da      aileron deflection
de      elevator deflection
dr      rudder deflection
|df      flap deflection
|df2    flap deflection for second set
|df3    flap deflection for third set
max     maximum
min     minimum

19) miscellaneous
recordRate              number of times to record data per second  [/s]
recordStartTime         time to start recording outpud data        [s]
dyn_on_speed            speed when dynamic pressure terms first computed [ft/s]
nondim_rate_V_rel_wind  use V_rel_wind to compute control rates    []
|simpleHingeMomentCoef  hinge moment coefficient                   []

(3) | [OPTIONAL DATA]
=====================

An input line may also be used to provide optional data that
will be used if provided but is not necessary for the code to 
operate.  As with the variable data described in section (2), multiple 
values or data files may be provided if the code is written to use 
them.

(4) # [COMMENTS]
================

Appended comments should be provided with each input line to indicate 
units on the variable in question and to indicate the source the data 
was drawn from.
**********************************************************************

**********************************************************************
III. Sample Input Lines:

CONSTANTS
=========

geometry bw   <value>   # geometric parameter, wingspan
Cm Cm_a       <value>   # stability derivative, d(Cm)/d(alpha)
controlSurface de <value> <value>  # max and min elevator deflections

LOOKUP TABLES
=============

CD CDfCL    <file.dat>  # CD(CL), drag polar data file
Cm Cmfade   <file.dat>  # Cm(alpha,delta_e), moment data file

HARD-CODED EQUATION
===================

CD CDfCL                # CD(CL), drag calculated in code based on CL
(none currently in use)

**********************************************************************

**********************************************************************
IV. Input Line Definitions:

Of all the possible permutations of variable names described above in
section II, only some are curently implemented in the code.  These are
described below.  Comments, denoted by '#,' are used to define the
lines and to indicate examples of the data if additional clarity is
needed for unique situations.  Again, those lines beginning with '|'
are not currently implemented in the code, but indicate planned
conventions in later versions.

# Key  Variable  Data      Units      Description                       Where Defined
#------------------------------------------------------------------------------------

init recordRate <recordRate> # [/s]   record data n times per second	uiuc_aircraft.h

# [s]   time to start recording output data				uiuc_aircraft.h
init recordStartTime <recordStartTime>

# []    use V_rel_wind to compute control rates (instead of U_body)     uiuc_aircraft.h
init nondim_rate_V_rel_wind <nondim_rate_V_rel_wind>

# [ft/s] speed at which dynamic pressure terms are first computed       uiuc_aircraft.h
init dyn_on_speed <dyn_on_speed>

init Dx_pilot <Dx_pilot> # [ft]       reference pilot x-position        ls_generic.h
init Dy_pilot <Dy_pilot> # [ft]       reference pilot y-position        ls_generic.h
init Dz_pilot <Dz_pilot> # [ft]       reference pilot z-position        ls_generic.h

# the following commands are currently conflicting with Flight
# Gear and are not working correctly:
|init Dx_cg <Dx_cg>      # [ft]       reference cg x_location           ls_generic.h
|init Dy_cg <Dy_cg>      # [ft]       reference cg y_location           ls_generic.h
|init Dz_cg <Dz_cg>      # [ft]       reference cg z_location           ls_generic.h
|init V_north <V_north>  # [ft/s]     initial local x-velocity          ls_generic.h
|init V_east <V_east>    # [ft/s]     initial local y-velocity          ls_generic.h
|init V_down <V_down>    # [ft/s]     initial local z-velocity          ls_generic.h
|init Altitude <Altitude> # [ft/s]    initial altitude                  ls_generic.h

init P_body <P_body>     # [rad/s]    initial roll rate                 ls_generic.h
init Q_body <Q_body>     # [rad/s]    initial pitch rate                ls_generic.h
init R_body <R_body>     # [rad/s]    initial yaw rate                  ls_generic.h
init Phi <Phi>           # [rad]      initial bank angle                ls_generic.h
init Theta <Theta>       # [rad]      initial pitch attitude angle      ls_generic.h
init Psi <Psi>           # [rad]      initial heading angle             ls_generic.h
init Long_trim <Long_trim> # [rad]    longitudinal trim                 ls_cockpit.h

geometry bw <bw>        # [ft]        wingspan                          uiuc_aircraft.h
geometry cbar <cbar>    # [ft]        wing mean aero chord              uiuc_aircraft.h
geometry Sw <Sw>        # [ft^2]      wing reference area               uiuc_aircraft.h
|geometry iw <iw>       # [deg]       wing incidence angle              uiuc_aircraft.h
|geometry bc <bc>       # [ft]        canard span                       uiuc_aircraft.h
|geometry cc <cc>       # [ft]        canard chord                      uiuc_aircraft.h
|geometry Sc <Sc>       # [sq-ft]     canard area                       uiuc_aircraft.h
|geometry ic <ic>       # [deg]       canard incidence angle            uiuc_aircraft.h
geometry bh <bh>        # [ft]        horizontal tail span              uiuc_aircraft.h
geometry ch <ch>        # [ft]        horizontal tail chord             uiuc_aircraft.h
geometry Sh <Sh>        # [sq-ft]     horizontal tail area              uiuc_aircraft.h
geometry ih <ih>        # [deg]       horiz tail incidence angle        uiuc_aircraft.h
|geometry bv <bv>       # [ft]        vertical tail span                uiuc_aircraft.h
|geometry cv <cv>       # [ft]        vertical tail chord               uiuc_aircraft.h
|geometry Sv <Sv>       # [sq-ft]     vertical tail area                uiuc_aircraft.h
|geometry iv <iv>       # [deg]       vert tail incidence angle         uiuc_aircraft.h

|controlSurface Se <Se>  # [ft^2]     elevator area                     uiuc_aircraft.h
|controlSurface Sa <Sa>  # [ft^2]     aileron area                      uiuc_aircraft.h
|controlSurface Sr <Sr>  # [ft^2]     rudder area                       uiuc_aircraft.h
|controlSurface Sf <Sf>  # [ft^2]     flap area                         uiuc_aircraft.h
controlSurface de <demax> <demin>   # [deg]  max/min elev deflections   uiuc_aircraft.h
controlSurface da <damax> <damin>   # [deg]  max/min ail deflections    uiuc_aircraft.h
controlSurface dr <drmax> <drmin>   # [deg]  max/min rud deflections    uiuc_aircraft.h
|controlSurface df <dfmax> <dfmin>  # [deg]  max/min flap deflections   uiuc_aircraft.h

# Note: Currently demin/damin/drmin are not used in the code, and the max/min is +-dema

# trim always set to some fixed input value (radians)             [rad] uiuc_aircraft.h
controlSurface set_Long_trim <elevator_tab>

# trim always set to some fixed input value (degrees)             [deg] uiuc_aircraft.h
controlSurface set_Long_trim_deg <elevator_tab>

controlSurface zero_Long_trim       # [deg]  trim always set to zero    uiuc_aircraft.h

# elevator step input with deflection angle [deg] and starting time [s] uiuc_aircraft.h
controlSurface elevator_step <elevator_step_angle> <elevator_step_startTime>

# elevator singlet input with deflection angle [deg], starting time [s],
# and duration of input [s]                                             uiuc_aircraft.h
controlSurface elevator_singlet <elevator_singlet_angle> ->
        <elevator_singlet_startTime> <elevator_singlet_duration>

# elevator doublet input with deflection angle [deg], starting time [s],
# and TOTAL duration of input (both up and down deflections) [s]        uiuc_aircraft.h
controlSurface elevator_doublet <elevator_doublet_angle> ->
        <elevator_doublet_startTime> <elevator_doublet_duration>

# tabulated elevator input (as function of time) with conversion
# factor codes and starting time [s]					uiuc_aircraft.h
controlSurface elevator_input <elevator_input_file> ->
        <token_value_convert1> <token_value_convert2> ->
	<elevator_input_startTime>


|controlsMixer nomix <?> # []         no controls mixing                uiuc_aircraft.h


mass Weight <Weight>    # [lb]        gross takeoff weight              uiuc_aircraft.h
mass Mass <Mass>        # [slug]      gross takeoff mass                ls_generic.h
mass I_xx <I_xx>        # [slug-ft^2] roll inertia                      ls_generic.h
mass I_yy <I_yy>        # [slug-ft^2] pitch inertia                     ls_generic.h
mass I_zz <I_zz>        # [slug-ft^2] yaw inertia                       ls_generic.h
mass I_xz <I_xz>        # [slug-ft^2] lateral cross inertia             ls_generic.h


# maximum and minimum engine thrust                             [lb]    uiuc_aircraft.h
|engine thrust <thrustMax> <thrustMin>

# simple single engine maximum thrust                           [lb]    uiuc_aircraft.h
engine simpleSingle <simpleSingleMaxThrust>

engine c172             # use Cessna 172 engine model of Tony Peden
engine cherokee         # use Piper Cherokee engine model


CL CLo <CLo>            # []          lift coef for all angles = 0      uiuc_aircraft.h
CL CL_a <CL_a>          # [/rad]      lift curve slope, d(CL)/d(alpha)  uiuc_aircraft.h
CL CL_adot <CL_adot>    # [/rad]      d(CL)/d(alpha)/da(time)           uiuc_aircraft.h
CL CL_q <CL_q>          # [/rad]      d(CL)/d(q)                        uiuc_aircraft.h
CL CL_ih <CL_ih>        # [/rad]      CL due to horiz tail incidence    uiuc_aircraft.h
CL CL_de <CL_de>        # [/rad]      d(CL)/d(de)                       uiuc_aircraft.h

# CL(alpha), conversion for CL, for alpha                           []  uiuc_aircraft.h
CL CLfa <CLfa.dat> <token_value_convert1> <token_value_convert2>

# CL(alpha,delta_e), conversion for CL, for alpha, for delta_e      []  uiuc_aircraft.h
CL CLfade <CLfade.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>

  # the following are lift coefficients in the body axis
CL CZo <CZo>            # []          lift coef for all angles = 0      uiuc_aircraft.h
CL CZ_a <Cz_a>          # [/rad]      lift curve slope, d(CZ)/d(alpha)  uiuc_aircraft.h
CL CZ_a2 <CZ_a2>        # [/rad]      d(CZ)/d(alpha squared)            uiuc_aircraft.h
CL CZ_a3 <CZ_a3>        # [/rad]      d(CZ)/d(alpha cubed)              uiuc_aircraft.h
CL CZ_adot <CZ_adot>    # [/rad]      d(CZ)/d(alpha)/d(time)            uiuc_aircraft.h
CL CZ_q <CZ_q>          # [/rad]      d(CZ)/d(q)                        uiuc_aircraft.h
CL CZ_de <CZ_de>        # [/rad]      d(CZ)/d(de)                       uiuc_aircraft.h
CL CZ_deb2 <CZ_deb2>    # [/rad]      d(CZ)/d(de, beta squared)         uiuc_aircraft.h
CL CZ_df <CZ_df>        # [/rad]      d(CZ)/d(df)                       uiuc_aircraft.h
CL CZ_adf <CZ_adf>      # [/rad]      d(CZ)/d(alpha, df)                uiuc_aircraft.h

|CL CLfCT <CLfCT.dat>   #             CL(thrust coef)                   uiuc_aircraft.h
|CL CLfRe               #             CL(Reynolds #), equation          uiuc_aircraft.h
|CL CL_afaM <CL_afaM.dat> #           CL_alpha(alpha,Mach #)            uiuc_aircraft.h
   # these are sample examples that might be used in later versions of the code


# note that CD terms must come after CL for induced drag to be computed
CD CDo <CDo>            # []          drag coef for all angles = 0      uiuc_aircraft.h
CD CDK <CDK>            # []          induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
CD CD_a <CD_a>          # [/rad]      d(CD)/d(alpha)                    uiuc_aircraft.h
CD CD_ih <CD_ih>        # [/rad]      CD due to horiz tail incidence    uiuc_aircraft.h
CD CD_de <CD_de>        # [/rad]      d(CD)/d(delta_e)                  uiuc_aircraft.h

# CD(alpha), conversion for CD, for alpha                           []  uiuc_aircraft.h
CD CDfa <CDfa.dat> <token_value_convert1> <token_value_convert2>

# CD(CL) drag polar, conversion for CD, for CL                      []  uiuc_aircraft.h
CD CDfCL <CDfCL.dat> <token_value_convert1> <token_value_convert2>

# CD(alpha,delta_e), conversion for CD, for alpha, for delta_e      []  uiuc_aircraft.h
CD CDfade <CDfade.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>

  # the following are drag coefficients in the body axis
CD CXo <CXo>            # []          drag coef for all angles = 0      uiuc_aircraft.h
CD CXK <CXK>            # []          induced drag constant 1/(pi*e*AR) uiuc_aircraft.h
CD CX_a <CX_a>          # [/rad]      d(CX)/d(alpha)                    uiuc_aircraft.h
CD CX_a2 <CX_a2>        # [/rad]      d(CX)/d(alpha squared)            uiuc_aircraft.h
CD CX_a3 <CX_a3>        # [/rad]      d(CX)/d(alpha cubed)              uiuc_aircraft.h
CD CX_q <CX_q>          # [/rad]      d(CX)/d(q)                        uiuc_aircraft.h
CD CX_de <CX_de>        # [/rad]      d(CX)/d(de)                       uiuc_aircraft.h
CD CX_dr <CX_dr>        # [/rad]      d(CX)/d(dr)                       uiuc_aircraft.h
CD CX_df <CX_df>        # [/rad]      d(CX)/d(df)                       uiuc_aircraft.h
CD CX_adf <CX_adf>      # [/rad]      d(CX)/d(alpha, df)                uiuc_aircraft.h


Cm Cmo <Cmo>            # []          pitch mom coef for all angles=0   uiuc_aircraft.h
Cm Cm_a <Cm_a>          # [/rad]      d(Cm)/d(alpha)                    uiuc_aircraft.h
Cm Cm_a2 <Cm_a2>        # [/rad]      d(Cm)/d(alpha squared)            uiuc_aircraft.h
Cm Cm_adot <Cm_adot>    # [/rad]      d(Cm)/d(alpha)/d(time)            uiuc_aircraft.h
Cm Cm_q <Cm_q>          # [/rad]      d(Cm)/d(q)                        uiuc_aircraft.h
Cm Cm_ih <Cm_ih>        # [/rad]      Cm due to horiz tail incidence    uiuc_aircraft.h
Cm Cm_de <Cm_de>        # [/rad]      d(Cm)/d(de)                       uiuc_aircraft.h
Cm Cm_de <Cm_b2>        # [/rad]      d(Cm)/d(beta squared)             uiuc_aircraft.h
Cm Cm_r <Cm_r>          # [/rad]      d(Cm)/d(r)                        uiuc_aircraft.h
Cm Cm_df <Cm_df>        # [/rad]      d(Cm)/d(df)                       uiuc_aircraft.h

# Cm(alpha), conversion for Cm, for alpha                           []  uiuc_aircraft.h
Cm Cmfa <Cmfa.dat> <token_value_convert1> <token_value_convert2>

# Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e      []  uiuc_aircraft.h
Cm Cmfade <Cmfade.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>


CY CYo <CYo>            # []          side-force coef for all angles=0  uiuc_aircraft.h
CY CY_beta <CY_beta>    # [/rad]      d(CY)/d(beta)                     uiuc_aircraft.h
CY CY_p <CY_p>          # [/rad]      d(CY)/d(p)                        uiuc_aircraft.h
CY CY_r <CY_r>          # [/rad]      d(CY)/d(r)                        uiuc_aircraft.h
CY CY_da <CY_da>        # [/rad]      d(CY)/d(da)                       uiuc_aircraft.h
CY CY_dr <CY_dr>        # [/rad]      d(CY)/d(dr)                       uiuc_aircraft.h
CY CY_dra <CY_dra>      # [/rad]      d(CY)/d(dr, alpha)                uiuc_aircraft.h
CY CY_dra <CY_bdot>     # [/rad]      d(CY)/d(beta)/d(time)             uiuc_aircraft.h

# CY(alpha,delta_a), conversion for CY, for alpha, for delta_a      []  uiuc_aircraft.h
CY CYfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>

# CY(beta,delta_r), conversion for CY, for beta, for delta_r        []  uiuc_aircraft.h
CY CYfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>


Cl Clo <Clo>            # []          roll mom coef for all angles=0    uiuc_aircraft.h
Cl Cl_beta <Cl_beta>    # [/rad]      d(Cl)/d(beta)                     uiuc_aircraft.h
Cl Cl_p <Cl_p>          # [/rad]      d(Cl)/d(p)                        uiuc_aircraft.h
Cl Cl_r <Cl_r>          # [/rad]      d(Cl)/d(r)                        uiuc_aircraft.h
Cl Cl_da <Cl_da>        # [/rad]      d(Cl)/d(da)                       uiuc_aircraft.h
Cl Cl_dr <Cl_dr>        # [/rad]      d(Cl)/d(dr)                       uiuc_aircraft.h
Cl Cl_daa <Cl_daa>      # [/rad]      d(Cl)/d(da, alpha)                uiuc_aircraft.h

# Cl(alpha,delta_a), conversion for Cl, for alpha, for delta_a      []  uiuc_aircraft.h
Cl Clfada <CYfada.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>

# Cl(beta,delta_r), conversion for Cl, for beta, for delta_r        []  uiuc_aircraft.h
Cl Clfbetadr <CYfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>


Cn Cno <Cno>            # []          yaw mom coef for all angles=0     uiuc_aircraft.h
Cn Cn_beta <Cn_beta>    # [/rad]      d(Cn)/d(beta)                     uiuc_aircraft.h
Cn Cn_p <Cn_p>          # [/rad]      d(Cn)/d(p)                        uiuc_aircraft.h
Cn Cn_r <Cn_r>          # [/rad]      d(Cn)/d(r)                        uiuc_aircraft.h
Cn Cn_da <Cn_da>        # [/rad]      d(Cn)/d(da)                       uiuc_aircraft.h
Cn Cn_dr <Cn_dr>        # [/rad]      d(Cn)/d(dr)                       uiuc_aircraft.h
Cn Cn_q <Cn_q>          # [/rad]      d(Cn)/d(q)                        uiuc_aircraft.h
Cn Cn_b3 <Cn_b3>        # [/rad]      d(Cn)/d(beta cubed)               uiuc_aircraft.h

# Cn(alpha,delta_a), conversion for Cn, for alpha, for delta_a      []  uiuc_aircraft.h
Cn Cnfada <Cnfada.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>

# Cn(beta,delta_r), conversion for Cn, for beta, for delta_r        []  uiuc_aircraft.h
Cn Cnfbetadr <Cnfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
          <token_value_convert3>

=============================CONVERSION CODES================================

To calculate the aero forces, angles (eg, alfa, beta, elevator deflection, etc)
must be in radians.  To convert input data in degree to radian, use a
conversion code of 1.  To use no conversion, use a conversion code of 0.

------------------------------------------------
convert1/2/3  Action
------------------------------------------------
  0           no conversion (multiply by 1)
  1           convert degrees to radians
=============================================================================

|gear kgear <kgear>     # []          gear spring constant(s)           uiuc_aircraft.h
|gear muRoll <muRoll>   # []          gear rolling friction coef(s)     uiuc_aircraft.h
|gear cgear <cgear>     # []          gear damping constant(s)          uiuc_aircraft.h
|gear strutLength <sL>  # [ft]        gear strut length                 uiuc_aircraft.h


ice iceTime <iceTime>   # [s]         time when icing begins            uiuc_aircraft.h

# [s]   period for eta_ice to reach eta_final				uiuc_aircraft.h
ice transientTime <transientTime>

# []    icing severity factor						uiuc_aircraft.h
ice eta_ice_final <eta_ice_final>

ice kCDo <kCDo>         # []          icing constant for CDo            uiuc_aircraft.h
ice kCDK <kCDo>         # []          icing constant for CDK            uiuc_aircraft.h
ice kCD_a <kCD_a>       # []          icing constant for CD_a           uiuc_aircraft.h
ice kCD_q <kCD_q>       # []          icing constant for CD_q           uiuc_aircraft.h
ice kCD_de <kCD_de>     # []          icing constant for CD_de          uiuc_aircraft.h
ice kCD_dr <kCD_dr>     # []          icing constant for CD_dr          uiuc_aircraft.h
ice kCD_df <kCD_df>     # []          icing constant for CD_df          uiuc_aircraft.h
ice kCD_adf <kCD_adf>   # []          icing constant for CD_adf         uiuc_aircraft.h

ice kCXo <kCXo>         # []          icing constant for CXo            uiuc_aircraft.h
ice kCXK <kCXo>         # []          icing constant for CXK            uiuc_aircraft.h
ice kCX_a <kCX_a>       # []          icing constant for CX_a           uiuc_aircraft.h
ice kCX_a2 <kCX_a2>     # []          icing constant for CX_a2          uiuc_aircraft.h
ice kCX_a3 <kCX_a3>     # []          icing constant for CX_a3          uiuc_aircraft.h
ice kCX_q <kCX_q>       # []          icing constant for CX_q           uiuc_aircraft.h
ice kCX_de <kCX_de>     # []          icing constant for CX_de          uiuc_aircraft.h
ice kCX_dr <kCX_dr>     # []          icing constant for CX_dr          uiuc_aircraft.h
ice kCX_df <kCX_df>     # []          icing constant for CX_df          uiuc_aircraft.h
ice kCX_adf <kCX_adf>   # []          icing constant for CX_adf         uiuc_aircraft.h

ice kCLo <kCLo>         # []          icing constant for CLo            uiuc_aircraft.h
ice kCL_a <kCL_a>       # []          icing constant for CL_a           uiuc_aircraft.h
ice kCL_adot <kCL_adot> # []          icing constant for CL_adot        uiuc_aircraft.h
ice kCL_q <kCL_q>       # []          icing constant for CL_q           uiuc_aircraft.h
ice kCL_de <kCL_de>     # []          icing constant for CL_de          uiuc_aircraft.h
ice kCL_df <kCL_df>     # []          icing constant for CL_df          uiuc_aircraft.h
ice kCL_adf <kCL_adf>   # []          icing constant for CL_adf         uiuc_aircraft.h

ice kCZo <kCZo>         # []          icing constant for CZo            uiuc_aircraft.h
ice kCZ_a <kCZ_a>       # []          icing constant for CZ_a           uiuc_aircraft.h
ice kCZ_a2 <kCZ_a2>     # []          icing constant for CZ_a2          uiuc_aircraft.h
ice kCZ_a3 <kCZ_a3>     # []          icing constant for CZ_a3          uiuc_aircraft.h
ice kCZ_adot <kCZ_adot> # []          icing constant for CZ_adot        uiuc_aircraft.h
ice kCZ_q <kCZ_q>       # []          icing constant for CZ_q           uiuc_aircraft.h
ice kCZ_de <kCZ_de>     # []          icing constant for CZ_de          uiuc_aircraft.h
ice kCZ_df <kCZ_df>     # []          icing constant for CZ_df          uiuc_aircraft.h
ice kCZ_adf <kCZ_adf>   # []          icing constant for CZ_adf         uiuc_aircraft.h
ice kCZ_deb2 <kCZ_deb2> # []          icing constant for CZ_deb2        uiuc_aircraft.h

ice kCmo <kCmo>         # []          icing constant for Cmo            uiuc_aircraft.h
ice kCm_a <kCm_a>       # []          icing constant for Cm_a           uiuc_aircraft.h
ice kCm_a2 <kCm_a2>     # []          icing constant for Cm_a2          uiuc_aircraft.h
ice kCm_a3 <kCm_a3>     # []          icing constant for Cm_a3          uiuc_aircraft.h
ice kCm_adot <kCm_adot> # []          icing constant for Cm_adot        uiuc_aircraft.h
ice kCm_q <kCm_q>       # []          icing constant for Cm_q           uiuc_aircraft.h
ice kCm_r <kCm_r>       # []          icing constant for Cm_r           uiuc_aircraft.h
ice kCm_de <kCm_de>     # []          icing constant for Cm_de          uiuc_aircraft.h
ice kCm_df <kCm_df>     # []          icing constant for Cm_df          uiuc_aircraft.h

ice kCYo <kCYo>         # []          icing constant for CYo            uiuc_aircraft.h
ice kCY_beta <kCy_beta> # []          icing constant for CY_beta        uiuc_aircraft.h
ice kCY_p <kCY_p>       # []          icing constant for CY_p           uiuc_aircraft.h
ice kCY_r <kCY_r>       # []          icing constant for CY_r           uiuc_aircraft.h
ice kCY_da <kCY_da>     # []          icing constant for CY_da          uiuc_aircraft.h
ice kCY_dr <kCY_dr>     # []          icing constant for CY_dr          uiuc_aircraft.h
ice kCY_dra <kCY_dra>   # []          icing constant for CY_dra         uiuc_aircraft.h
ice kCY_bdot <kCY_bdot> # []          icing constant for CY_bdot        uiuc_aircraft.h

ice kClo <kClo>         # []          icing constant for Clo            uiuc_aircraft.h
ice kCl_beta <kCl_beta> # []          icing constant for Cl_beta        uiuc_aircraft.h
ice kCl_p <kCl_p>       # []          icing constant for Cl_p           uiuc_aircraft.h
ice kCl_r <kCl_r>       # []          icing constant for Cl_r           uiuc_aircraft.h
ice kCl_da <kCl_da>     # []          icing constant for Cl_da          uiuc_aircraft.h
ice kCl_dr <kCl_dr>     # []          icing constant for Cl_dr          uiuc_aircraft.h
ice kCl_daa <kCl_daa>   # []          icing constant for Cl_daa         uiuc_aircraft.h

ice kCno <kCno>         # []          icing constant for Cno            uiuc_aircraft.h
ice kCn_beta <kCn_beta> # []          icing constant for Cn_beta        uiuc_aircraft.h
ice kCn_b3 <kCn_b3>     # []          icing constant for Cn_b3          uiuc_aircraft.h
ice kCn_p <kCn_p>       # []          icing constant for Cn_p           uiuc_aircraft.h
ice kCn_q <kCn_q>       # []          icing constant for Cn_q           uiuc_aircraft.h
ice kCn_r <kCn_r>       # []          icing constant for Cn_r           uiuc_aircraft.h
ice kCn_da <kCn_da>     # []          icing constant for Cn_da          uiuc_aircraft.h
ice kCn_dr <kCn_dr>     # []          icing constant for Cn_dr          uiuc_aircraft.h

ice beta_probe_wing <x_probe_wing> #  wing flow angle probe location    uiuc_aircraft.h
ice beta_probe_wing <x_probe_tail> #  tail flow angle probe location    uiuc_aircraft.h


record Simtime                # [s]       current sim time              global
record dt                     # [s]       current time step             global
record Weight                 # [lb]      aircraft gross takeoff weight uiuc_aircraft.h
record Mass                   # [slug]    aircraft mass                 ls_generic.h
record I_xx                   # [slug-ft^2] roll inertia                ls_generic.h
record I_yy                   # [slug-ft^2] pitch inertia               ls_generic.h
record I_zz                   # [slug-ft^2] yaw inertia                 ls_generic.h
record I_xz                   # [slug-ft^2] lateral cross inertia       ls_generic.h
record Dx_pilot               # [ft]      reference pilot x-location    ls_generic.h
record Dy_pilot               # [ft]      reference pilot y-location    ls_generic.h
record Dz_pilot               # [ft]      reference pilot z-location    ls_generic.h
record Dx_cg                  # [ft]      cg x_location                 ls_generic.h
record Dy_cg                  # [ft]      cg y_location                 ls_generic.h
record Dz_cg                  # [ft]      cg z_location                 ls_generic.h
record Lat_geocentric         # [rad]     geocentric latitude           ls_generic.h
record Lon_geocentric         # [rad]     geocentric longitude          ls_generic.h
record Radius_to_vehicle      # [ft]      geocentric distance           ls_generic.h
record Latitude               # [rad]     geodetic latitude             ls_generic.h
record Longitude              # [rad]     geodetic longitude            ls_generic.h
record Altitude               # [ft]      geodetic altitude             ls_generic.h
record Phi                    # [rad]     Euler bank angle              ls_generic.h
record Theta                  # [rad]     Euler pitch attitude angle    ls_generic.h
record Psi                    # [rad]     Euler heading angle           ls_generic.h
record V_dot_north            # [ft/s^2]  local x-acceleration          ls_generic.h
record V_dot_east             # [ft/s^2]  local y-acceleration          ls_generic.h
record V_dot_down             # [ft/s^2]  local z-acceleration          ls_generic.h
record U_dot_body             # [ft/s^2]  body x-acceleration           ls_generic.h
record V_dot_body             # [ft/s^2]  body y-acceleration           ls_generic.h
record W_dot_body             # [ft/s^2]  body z-acceleration           ls_generic.h
record A_X_pilot              # [ft/s^2]  pilot x-acceleration          ls_generic.h
record A_Y_pilot              # [ft/s^2]  pilot y-acceleration          ls_generic.h
record A_Z_pilot              # [ft/s^2]  pilot z-acceleration          ls_generic.h
record A_X_cg                 # [ft/s^2]  cg x-acceleration             ls_generic.h
record A_Y_cg                 # [ft/s^2]  cg y-acceleration             ls_generic.h
record A_Z_cg                 # [ft/s^2]  cg z-acceleration             ls_generic.h
record N_X_pilot              # [ft/s^2]  pilot x-acceleration          ls_generic.h
record N_Y_pilot              # [ft/s^2]  pilot y-acceleration          ls_generic.h
record N_Z_pilot              # [ft/s^2]  pilot z-acceleration          ls_generic.h
record N_X_cg                 # [ft/s^2]  cg x-acceleration             ls_generic.h
record N_Y_cg                 # [ft/s^2]  cg y-acceleration             ls_generic.h
record N_Z_cg                 # [ft/s^2]  cg z-acceleration             ls_generic.h
record P_dot_body             # [rad/s^2] roll rate acceleration        ls_generic.h
record Q_dot_body             # [rad/s^2] pitch rate acceleration       ls_generic.h
record R_dot_body             # [rad/s^2] yaw rate acceleration         ls_generic.h
record V_north                # [ft/s]    local x-velocity              ls_generic.h
record V_east                 # [ft/s]    local y-velocity              ls_generic.h
record V_down                 # [ft/s]    local z-velocity              ls_generic.h
record V_north_rel_ground     # [ft/s]    local x-velocity wrt ground   ls_generic.h
record V_east_rel_ground      # [ft/s]    local y-velocity wrt ground   ls_generic.h
record V_down_rel_ground      # [ft/s]    local z-velocity wrt ground   ls_generic.h
record V_north_airmass        # [ft/s]    local x-velocity of airmass   ls_generic.h
record V_east_airmass         # [ft/s]    local y-velocity of airmass   ls_generic.h
record V_down_airmass         # [ft/s]    local z-velocity of airmass   ls_generic.h
record V_north_rel_airmass    # [ft/s]    local x-velocity wrt airmass  ls_generic.h
record V_east_rel_airmass     # [ft/s]    local y-velocity wrt airmass  ls_generic.h
record V_down_rel_airmass     # [ft/s]    local z-velocity wrt airmass  ls_generic.h
record U_gust                 # [ft/s]    local turbulence x-velocity   ls_generic.h
record V_gust                 # [ft/s]    local turbulence y-velocity   ls_generic.h
record W_gust                 # [ft/s]    local turbulence z-velocity   ls_generic.h
record U_body                 # [ft/s]    wind x-velocity in body axis  ls_generic.h
record V_body                 # [ft/s]    wind y-velocity in body axis  ls_generic.h
record W_body                 # [ft/s]    wind z-velocity in body axis  ls_generic.h
record V_rel_wind             # [ft/s]    total freestream velocity     ls_generic.h
record V_true_kts             # [kts]     true velocity                 ls_generic.h
record V_rel_ground           # [ft/s]    total velocity wrt ground     ls_generic.h
record V_inertial             # [ft/s]    total inertial velocity       ls_generic.h
record V_ground_speed         # [ft/s]    airspeed wrt ground           ls_generic.h
record V_equiv                # [ft/s]    equivalent airspeed           ls_generic.h
record V_equiv_kts            # [kts]     equivalent airspeed           ls_generic.h
record V_calibrated           # [ft/s]    calibrated airspeed           ls_generic.h
record V_calibrated_kts       # [kts]     calibrated airspeed           ls_generic.h
record P_local                # [rad/s]   local roll rate               ls_generic.h
record Q_local                # [rad/s]   local pitch rate              ls_generic.h
record R_local                # [rad/s]   local yaw rate                ls_generic.h
record P_body                 # [rad/s]   body roll rate                ls_generic.h
record Q_body                 # [rad/s]   body pitch rate               ls_generic.h
record R_body                 # [rad/s]   body yaw rate                 ls_generic.h
record P_total                # [rad/s]   total roll rate               ls_generic.h
record Q_total                # [rad/s]   total pitch rate              ls_generic.h
record R_total                # [rad/s]   total yaw rate                ls_generic.h
record Phi_dot                # [rad/s]   bank angle rate               ls_generic.h
record Theta_dot              # [rad/s]   pitch attitude angle rate     ls_generic.h
record Psi_dot                # [rad/s]   heading angle rate            ls_generic.h
record Latitude_dot           # [rad/s]   latitude rate                 ls_generic.h
record Longitude_dot          # [rad/s]   longitude rate                ls_generic.h
record Radius_dot             # [rad/s]   radius rate                   ls_generic.h
record Alpha                  # [rad]     angle of attack               ls_generic.h
record Alpha_deg              # [deg]     angle of attack (in degrees)  uiuc_aircraft.h
record Alpha_dot              # [rad/s]   rate of change of alpha       ls_generic.h
record Alpha_dot_deg          # [rad/s]   rate of change of alpha       uiuc_aircraft.h
record Beta                   # [rad]     sideslip angle                ls_generic.h
record Beta_deg               # [rad]     sideslip angle                uiuc_aircraft.h
record Beta_dot               # [rad/s]   rate of change of beta        ls_generic.h
record Beta_dot_deg           # [rad/s]   rate of change of beta        uiuc_aircraft.h
record Gamma_vert             # [rad]     vertical flight path angle    ls_generic.h
record Gamma_vert_deg         # [deg]     vertical flight path angle    uiuc_aircraft.h
record Gamma_horiz            # [rad]     horizontal flight path angle  ls_generic.h
record Gamma_horiz_deg        # [deg]     horizontal flight path angle  uiuc_aircraft.h
record Density                # [slug/ft^3] air density                 ls_generic.h
record V_sound                # [ft/s]    speed of sound                ls_generic.h
record Mach_number            # []        Mach number                   ls_generic.h
record Static_pressure        # [lb/ft^2] static pressure               ls_generic.h
record Total_pressure         # [lb/ft^2] total pressure                ls_generic.h
record Impact_pressure        # [lb/ft^2] impact pressure               ls_generic.h
record Dynamic_pressure       # [lb/ft^2] dynamic pressure              ls_generic.h
record Static_temperature     # [?]       static temperature            ls_generic.h
record Total_temperature      # [?]       total temperature             ls_generic.h
record Gravity                # [ft/s^2]  acceleration due to gravity   ls_generic.h
record Sea_level_radius       # [ft]      Earth radius                  ls_generic.h
record Earth_position_angle   # [rad]     Earth rotation angle          ls_generic.h
record Runway_altitude        # [ft]      runway altitude               ls_generic.h
record Runway_latitude        # [rad]     runway latitude               ls_generic.h
record Runway_longitude       # [rad]     runway longititude            ls_generic.h
record Runway_heading         # [rad]     runway heading                ls_generic.h
record Radius_to_rwy          # [ft]      geocentric radius to runway   ls_generic.h
record D_pilot_north_of_rwy   # [ft]      local pilot x-dist from rwy   ls_generic.h
record D_pilot_east_of_rwy    # [ft]      local pilot y-dist from rwy   ls_generic.h
record D_pilot_down_of_rwy    # [ft]      local pilot z-dist from rwy   ls_generic.h
record X_pilot_rwy            # [ft]      pilot x-dist from rwy         ls_generic.h
record Y_pilot_rwy            # [ft]      pilot y-dist from rwy         ls_generic.h
record H_pilot_rwy            # [ft]      pilot z-dist from rwy         ls_generic.h
record D_cg_north_of_rwy      # [ft]      local cg x-dist from rwy      ls_generic.h
record D_cg_east_of_rwy       # [ft]      local cg y-dist from rwy      ls_generic.h
record D_cg_down_of_rwy       # [ft]      local cg z-dist from rwy      ls_generic.h
record X_cg_rwy               # [ft]      cg x-dist from rwy            ls_generic.h
record Y_cg_rwy               # [ft]      cg y-dist from rwy            ls_generic.h
record H_cg_rwy               # [ft]      cg z-dist from rwy            ls_generic.h
record Throttle_pct           # [%]       throttle input                ls_cockpit.h
record Throttle_3             # [%]       throttle deflection           ls_cockpit.h
record Long_control           # []        pitch input                   ls_cockpit.h
record Long_trim              # [rad]     longitudinal trim             ls_cockpit.h
record Long_trim_deg          # [deg]     longitudinal trim             uiuc_aircraft.h
record elevator               # [rad]     elevator deflection           uiuc_aircraft.h
record elevator_deg           # [deg]     elevator deflection           uiuc_aircraft.h
record Lat_control            # []        roll input                    ls_cockpit.h
record aileron                # [rad]     aileron deflection            uiuc_aircraft.h
record aileron_deg            # [deg]     aileron deflection            uiuc_aircraft.h
record Rudder_pedal           # []        yaw input                     ls_cockpit.h
record rudder                 # [rad]     rudder deflection             uiuc_aircraft.h
record rudder_deg             # [deg]     rudder deflection             uiuc_aircraft.h
record CDfaI                  # []        CD(alpha)                     uiuc_aircraft.h
record CDfCLI                 # []        CD(CL), drag polar            uiuc_aircraft.h
record CDfadeI                # []        CD(alpha,delta_e)             uiuc_aircraft.h
record CD                     # []        drag coefficient              uiuc_aircraft.h
record CLfaI                  # []        CL(alpha)                     uiuc_aircraft.h
record CLfadeI                # []        CL(alpha,delta_e)             uiuc_aircraft.h
record CL                     # []        lift coefficient              uiuc_aircraft.h
record CmfaI                  # []        Cm(alpha)                     uiuc_aircraft.h
record CmfadeI                # []        Cm(alpha,delta_e)             uiuc_aircraft.h
record Cm                     # []        pitch moment coefficient      uiuc_aircraft.h
record CYfadaI                # []        CY(alpha,delta_a)             uiuc_aircraft.h
record CYfbetadrI             # []        CY(beta,delta_r)              uiuc_aircraft.h
record CY                     # []        side-force coefficient        uiuc_aircraft.h
record ClfadaI                # []        Cl(alpha,delta_a)             uiuc_aircraft.h
record ClfbetadrI             # []        Cl(beta,delta_r)              uiuc_aircraft.h
record Cl                     # []        roll moment coefficient       uiuc_aircraft.h
record CnfadaI                # []        Cn(alpha,delta_a)             uiuc_aircraft.h
record CnfbetadrI             # []        Cn(beta,delta_r)              uiuc_aircraft.h
record Cn                     # []        yaw moment coefficient        uiuc_aircraft.h
record CLclean_wing           # []        wing clean lift coefficient   uiuc_aircraft.h
record CLiced_wing            # []        wing iced lift coefficient    uiuc_aircraft.h
record CLclean_tail           # []        tail clean lift coefficient   uiuc_aircraft.h
record CLiced_tail            # []        tail iced lift coefficient    uiuc_aircraft.h
record Lift_clean_wing        # [lb]      wing clean lift force         uiuc_aircraft.h
record Lift_iced_wing         # [lb]      wing iced lift force          uiuc_aircraft.h
record Lift_clean_tail        # [lb]      tail clean lift force         uiuc_aircraft.h
record Lift_iced_tail         # [lb]      tail iced lift force          uiuc_aircraft.h
record Gamma_clean_wing       # [ft^2/s]  wing clean circulation        uiuc_aircraft.h
record Gamma_iced_wing        # [ft^2/s]  wing iced circulation         uiuc_aircraft.h
record Gamma_clean_tail       # [ft^2/s]  tail clean circulation        uiuc_aircraft.h
record Gamma_iced_tail        # [ft^2/s]  tail iced circulation         uiuc_aircraft.h
record w_clean_wing           # [ft/s]    wing clean downwash           uiuc_aircraft.h
record w_iced_wing            # [ft/s]    wing iced downwash            uiuc_aircraft.h
record w_clean_tail           # [ft/s]    tail clean downwash           uiuc_aircraft.h
record w_iced_tail            # [ft/s]    tail iced downwash            uiuc_aircraft.h
record V_total_clean_wing     # [ft/s]    wing clean velocity           uiuc_aircraft.h
record V_total_iced_wing      # [ft/s]    wing iced velocity            uiuc_aircraft.h
record V_total_clean_tail     # [ft/s]    tail clean velocity           uiuc_aircraft.h
record V_total_iced_tail      # [ft/s]    tail iced velocity            uiuc_aircraft.h
record beta_flow_clean_wing   # [rad]     wing clean flow angle         uiuc_aircraft.h
record beta_flow_clean_wing_deg # [deg]   wing clean flow angle         uiuc_aircraft.h
record beta_flow_iced_wing    # [rad]     wing iced flow angle          uiuc_aircraft.h
record beta_flow_iced_wing_deg # [deg]    wing iced flow angle          uiuc_aircraft.h
record beta_flow_clean_tail   # [rad]     tail clean flow angle         uiuc_aircraft.h
record beta_flow_clean_tail_deg # [deg]   tail clean flow angle         uiuc_aircraft.h
record beta_flow_iced_tail    # [rad]     tail iced flow angle          uiuc_aircraft.h
record beta_flow_iced_tail_deg # [deg]    tail iced flow angle          uiuc_aircraft.h
record Dbeta_flow_wing        # [rad]     difference in wing flow angle uiuc_aircraft.h
record Dbeta_flow_wing_deg    # [deg]     difference in wing flow angle uiuc_aircraft.h
record Dbeta_flow_tail        # [rad]     difference in tail flow angle uiuc_aircraft.h
record Dbeta_flow_tail_deg    # [deg]     difference in tail flow angle uiuc_aircraft.h
record pct_beta_flow_wing     # [%]       difference in wing flow angle uiuc_aircraft.h
record pct_beta_flow_tail     # [%]       difference in tail flow angle uiuc_aircraft.h
record F_X_wind               # [lb]      aero x-force in wind-axes     ls_generic.h
record F_Y_wind               # [lb]      aero y-force in wind-axes     ls_generic.h
record F_Z_wind               # [lb]      aero z-force in wind-axes     ls_generic.h
record F_X_aero               # [lb]      aero x-force in body-axes     ls_generic.h
record F_Y_aero               # [lb]      aero y-force in body-axes     ls_generic.h
record F_Z_aero               # [lb]      aero z-force in body-axes     ls_generic.h
record F_X_engine             # [lb]      prop x-force in body-axes     ls_generic.h
record F_Y_engine             # [lb]      prop y-force in body-axes     ls_generic.h
record F_Z_engine             # [lb]      prop z-force in body-axes     ls_generic.h
record F_X_gear               # [lb]      gear x-force in body-axes     ls_generic.h
record F_Y_gear               # [lb]      gear y-force in body-axes     ls_generic.h
record F_Z_gear               # [lb]      gear z-force in body-axes     ls_generic.h
record F_X                    # [lb]      total x-force in body-axes    ls_generic.h
record F_Y                    # [lb]      total y-force in body-axes    ls_generic.h
record F_Z                    # [lb]      total z-force in body-axes    ls_generic.h
record F_nort                 # [lb]      total x-force in local-axes   ls_generic.h
record F_east                 # [lb]      total y-force in local-axes   ls_generic.h
record F_down                 # [lb]      total z-force in local-axes   ls_generic.h
record M_l_aero               # [ft-lb]   aero roll mom in body axes    ls_generic.h
record M_m_aero               # [ft-lb]   aero pitch mom in body axes   ls_generic.h
record M_n_aero               # [ft-lb]   aero yaw mom in body axes     ls_generic.h
record M_l_engine             # [ft-lb]   prop roll mom in body axes    ls_generic.h
record M_m_engine             # [ft-lb]   prop pitch mom in body axes   ls_generic.h
record M_n_engine             # [ft-lb]   prop yaw mom in body axes     ls_generic.h
record M_l_gear               # [ft-lb]   gear roll mom in body axes    ls_generic.h
record M_m_gear               # [ft-lb]   gear pitch mom in body axes   ls_generic.h
record M_n_gear               # [ft-lb]   gear yaw mom in body axes     ls_generic.h
record M_l_rp                 # [ft-lb]   total roll mom in body axes   ls_generic.h
record M_m_rp                 # [ft-lb]   total pitch mom in body axes  ls_generic.h
record M_n_rp                 # [ft-lb]   total yaw mom in body axes    ls_generic.h


# the following command is implemented but the data is not used in any
# equation of motion
# hinge moment coefficient                                      []      uiuc_aircraft.h
|misc simpleHingeMomentCoef <simpleHingeMomentCoef>

**********************************************************************

**********************************************************************
V. Mandatory Input:

The following data is required for the simulator to function;
otherwise either the UIUC Aero Model or LaRCsim parts of the code will
probably crash.

1) aircraft geometry   (UIUC Aero Model)
bw        wingspan                       [ft]
cbar      mean aerodynamic chord         [ft]
Sw        wing planform area             [ft^2]

2) engine properties   (UIUC Engine Model)
(some engine model must be specified, such as...)
engine simpleSingle
          <or>
engine c172

3) mass variables   (LaRCsim)
Weight    aircraft gross takeoff weight  [lb]
          <or>
Mass      aircraft mass                  [slug]
I_xx      roll inertia                   [slug-ft^2]
I_yy      pitch inertia                  [slug-ft^2]
I_zz      yaw inertia                    [slug-ft^2]
I_xz      lateral cross inertia          [slug-ft^2]

4) aerodynamic force/moment components   (Aero Model)
CLo       lift coef for all angles = 0   []
CL_a      lift curve slope, d(CL)/d(alpha) [/rad]
CDo       drag coef for all angles = 0   []
CDK       induced drag constant          []
          <or>
CD_a      d(CD)/d(alpha)                 [/rad]
Cmo       pitch mom coef for all angles=0 []
Cm_a      d(Cm)/d(alpha)                 [/rad]
CY_beta   d(CY)/d(beta)                  [/rad]
Cl_beta   d(Cl)/d(beta)                  [/rad]
Cn_beta   d(Cn)/d(beta)                  [/rad]

5) gear properties   (none yet)

With the current version, the C172 model gear model is used for *ALL*
aircraft.  This can produce some interesting effects with heavy
aircraft (eg, Convair model), and light aircraft (eg, Pioneer UAV)

**********************************************************************
