* *
* FGFS Reconfigurable Aircraft Flight Model *
* Input File Documentation *
-* Version 0.63, March 17, 2000 *
+* Version 0.81, September 14, 2001 *
* *
* Authors: *
-* Jeff Scott (jscott@uiuc.edu) *
+* Jeff Scott (jscott@mail.com) *
* Bipin Sehgal (bsehgal@uiuc.edu) *
+* Robert Deters (rdeters@uiuc.edu) *
* Michael Selig (m-selig@uiuc.edu) *
* Dept of Aero and Astro Engineering *
* University of Illinois at Urbana-Champaign *
* *
************************************************
-
+
+**********************************************************************
+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.
+ Viewing this file in emacs makefile-mode with color makes this file
+ easier to read.
**********************************************************************
**********************************************************************
| 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
Examples input lines include
-Cm Cmo 0.194 # [] Bray pg 33
-Cm Cm_a -2.12 # [/rad] Bray pg 33
-CL CLfa CLfa.dat # [] Bray pg 50, Table 4.7
+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
(1) KEYWORDS
============
-There currently exist 15 types of variable keywords:
+There currently exist the following variable keyword types:
init Initial values for equation of motion
geometry Aircraft-specific geometric quantities
CY Aerodynamic y-force quantities (lateral)
Cl Aerodynamic l-moment quantities (lateral)
Cn Aerodynamic n-moment quantities (lateral)
-|gear Landing gear model quantities
-ice Aircraft icing model parameters
-record Record desired quantities to the file: uiuc_record.dat
+gear Landing gear model quantities
+ice Icing model parameters
+record Record desired quantites to file
+misc Miscellaneous inputs
+fog Fog field quantities
As each line of the input file is read, the code recognizes the
keyword, enters the appropriate switch statement in the code, and
Several of these variable names are not currently used.
1) variable class
-_ denotes stability derivative to be multiple by something
-f "function of" (indicates an m*n matrix data table is given)
+_ 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 state variables
-Dx_pilot x-location [ft]
-Dy_pilot y-location [ft]
-Dz_pilot z-location [ft]
-Dx_cg center of gravity x-location [ft]
-Dy_cg center of gravity y-location [ft]
-Dz_cg center of gravity z-location [ft]
-V_north x-velocity [ft/s]
-V_east y-velocity [ft/s]
-V_down z-velocity [ft/s]
-V_rel_wind total velocity [ft/s]
-Dynamic_pressure dynamic pressure [lb/ft^2]
-Alpha angle of attack [rad]
-Alpha_dot rate of change of alpha [rad/s]
-Beta sideslip angle [rad]
-Beta_dot rate of change of beta [rad]
-Gamma flight path angle [rad]
-P_body roll rate [rad/s]
-Q_body pitch rate [rad/s]
-R_body yaw rate [rad/s]
-Phi bank angle [rad]
-Theta pitch attitude angle [rad]
-Theta_dot rate change of theta [rad/s]
-Psi heading angle [rad]
-|long_trim
-|trim_inc
-M Mach number []
-Re Reynolds number []
-
-4) atmosphere properties
-Density air density [slug/ft^3]
-
-5) 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]
-
-6) control surface properties
-Sa aileron area [ft^2]
-Se elevator area [ft^2]
-Sf flap area [ft^2]
-Sr rudder area [ft^2]
-Lat_control roll control input [?]
-Long_control pitch control input [?]
-Rudder_pedal yaw control input [?]
-aileron aileron deflection [rad]
-elevator elevator deflection [rad]
-rudder rudder deflection [rad]
-|flap flap deflection [rad]
-
-7) mass variables
-|Weight gross takeoff weight [lb]
-Mass aircraft mass (used by LaRC) [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]
-
-8) engine/propulsion variables
-|thrust thrust [lb]
-simpleSingle simple single engine max thrust [lb]
-|Throttle_pct throttle input [] # ie, this is the stick
-|Throttle[3] throttle deflection [%] # this is what gets used to determine thrust
-
-9) 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 []
-
-10) 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 [lb]
-F_Y total y-force [lb]
-F_Z total z-force [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]
-
-11) landing gear properties
-|cgear gear damping constant [?]
-|kgear gear spring constant [?]
-|muGear gear rolling friction coef [?]
-|strutLength gear strut length [ft]
-
-12) icing model paramters
+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]
+aileron_input_file file of aileron deflections vs. time [s,deg]
+rudder_input_file file of rudder 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
+Dx_gear x-offset from CG [ft]
+Dy_gear y-offset from CG [ft]
+Dz_gear z-offset from CG [ft]
+cgear gear damping constant [lb/ft/s]
+kgear gear spring constant [lb/ft]
+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_final icing severity factor at end of transient time [-]
-kCA icing constants for associated aero coef. [-] (see IV)
+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]
-13) subscripts
+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
-|betadot rate change in beta
+b2 beta squared
+b3 beta cubed
+bdot rate change in beta
p roll rate
q pitch rate
r yaw rate
da aileron deflection
de elevator deflection
dr rudder deflection
-df flap deflection
+|df flap deflection
|df2 flap deflection for second set
|df3 flap deflection for third set
max maximum
min minimum
-(3) | (OPTIONAL DATA)
+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 []
+
+20) fog
+fog_segments number of fog points following this line
+fog_points fog intensity and the time at which it occurs
+
+(3) | [OPTIONAL DATA]
=====================
An input line may also be used to provide optional data that
values or data files may be provided if the code is written to use
them.
-(4) # (COMMENTS)
+(4) # [COMMENTS]
================
Appended comments should be provided with each input line to indicate
CONSTANTS
=========
-geometry bw <value> # geometric parameter, wingspan
-Cm Cm_a <value> # stability derivative, d(Cm)/d(alpha)
+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
+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. Definitions of Input Lines Currently Available:
+IV. Input Line Definitions:
-Of all the possible permutation of variable names described above in
-section II, only some are currently implemented in the code. These
-are described below. Comments, denoted by '#,' are used to define the
+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
# Key Variable Data Units Description Where Defined
#------------------------------------------------------------------------------------
-init Dx_pilot <Dx_pilot> # [ft] initial x-position ls_generic.h
-init Dy_pilot <Dy_pilot> # [ft] initial y-position ls_generic.h
-init Dz_pilot <Dz_pilot> # [ft] initial z-position ls_generic.h
-init Dx_cg <Dx_cg> # [ft] initial cg x_location ls_generic.h
-init Dy_cg <Dy_cg> # [ft] initial cg y_location ls_generic.h
-init Dz_cg <Dz_cg> # [ft] initial cg z_location ls_generic.h
-|init V_north <V_north> # [ft/s] initial x-velocity ls_generic.h
-|init V_east <V_east> # [ft/s] initial y-velocity ls_generic.h
-|init V_down <V_down> # [ft/s] initial z-velocity ls_generic.h
+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 U_body <U_body> # [ft/s] initial x-velocity in body axis ls_generic.h
+init V_body <V_body> # [ft/s] initial y-velocity in body axis ls_generic.h
+init W_body <W_body> # [ft/s] initial z-velocity in body axis 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 Alpha <Alpha> # [deg] initial angle of attack ls_generic.h
+init Beta <Beta> # [deg] initial side slip 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 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 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
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 is not used in the code, and the max/min is +-demax.
+# trim always set to some fixed input value (radians) [rad] uiuc_aircraft.h
+controlSurface set_Long_trim <elevator_tab>
+# Note: Do not use. Only works with pilot_elev_no and elevator_input. Use an elevator input file instead
+
+# trim always set to some fixed input value (degrees) [deg] uiuc_aircraft.h
+controlSurface set_Long_trim_deg <elevator_tab>
+# Note: Do not use. Only works with pilot_elev_no and elevator_input. Use an elevator input file instead
+
+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>
+
+# tabulated aileron input (as function of time) with conversion
+# factor codes and starting time [s] uiuc_aircraft.h
+controlSurface aileron_input <aileron_input_file> ->
+ <token_value_convert1> <token_value_convert2> ->
+ <aileron_input_startTime>
+
+# tabulated rudder input (as function of time) with conversion
+# factor codes and starting time [s] uiuc_aircraft.h
+controlSurface rudder_input <rudder_input_file> ->
+ <token_value_convert1> <token_value_convert2> ->
+ <rudder_input_startTime>
+
+# ignore elevator input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
+controlSurface pilot_elev_no
+# Note: Only works if elevator_input is used
+
+# ignore aileron input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
+controlSurface pilot_ail_no
+# Note: Only works if aileron_input is used
+
+# ignore rudder input from the joystick/keyboard/mouse [-] uiuc_aircraf.h
+controlSurface pilot_rud_no
+# Note: Only works if rudder_input is used
|controlsMixer nomix <?> # [] no controls mixing uiuc_aircraft.h
-|mass Weight <Weight> # [lb] gross takeoff weight (not used)
+
+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
-|engine thrust <thrustMax> <thrustMin> # [lb] max/min engine thrust uiuc_aircraft.h
-engine simpleSingle <sSMaxThrust> # [lb] simple single engine uiuc_aircraft.h
-engine c172 # use Cessna 172 engine model of Tony Peden
+
+# 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)/delta(q) 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> <conversion1> <conversion2>
+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> <conversion1> <conversion2> <conversion3>
+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
+
+# CZ(alpha), conversion for CZ, for alpha [] uiuc_aircraft.h
+CL CZfa <CZfa.dat> <token_value_convert1> <token_value_convert2>
|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
-# there are examples that might later be included in the code
+ # 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> # [] constant, as in CD=CDo+K*CL^2 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> <conversion1> <conversion2>
+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> <conversion1> <conversion2> <conversion3>
+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 Cmfa <Cmfa.dat> # [] Cm(alpha) uiuc_aircraft.h
-Cm Cmfade <Cmfade.dat> # [] Cm(alpha,delta_e) 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> <conversion1> <conversion2> <conversion3>
+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(delta_a) uiuc_aircraft.h
-CY CY_dr <CY_dr> # [/rad] d(CY)/d(delta_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> <conversion1> <conversion2> <conversion3>
+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> <conversion1> <conversion2> <conversion3>
+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_betafCL # [/rad] Cl_beta(CL) equation 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_rfCL # [/rad] Cl_r(CL) equation uiuc_aircraft.h
-Cl Cl_da <Cl_da> # [/rad] d(Cl)/d(delta_a) uiuc_aircraft.h
-Cl Cl_dr <Cl_dr> # [/rad] d(Cl)/d(delta_r) uiuc_aircraft.h
-Cl Clfada # [] Cl(alpha,delta_a), equation 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> <conversion1> <conversion2> <conversion3>
+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> <conversion1> <conversion2> <conversion3>
+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_betafCL # [/rad] Cn_beta(CL) equation uiuc_aircraft.h
Cn Cn_p <Cn_p> # [/rad] d(Cn)/d(p) uiuc_aircraft.h
-Cn Cn_pfCL # [/rad] Cn_p(CL) equation uiuc_aircraft.h
Cn Cn_r <Cn_r> # [/rad] d(Cn)/d(r) uiuc_aircraft.h
-Cn Cn_rfCL # [/rad] Cn_r(CL) equation 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_drfCL # [/rad] Cn_dr(CL) equation 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> <conversion1> <conversion2> <conversion3>
+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> <conversion1> <conversion2> <conversion3>
+Cn Cnfbetadr <Cnfbetadr.dat> <token_value_convert1> <token_value_convert2> ->
+ <token_value_convert3>
=============================CONVERSION CODES================================
conversion code of 1. To use no conversion, use a conversion code of 0.
------------------------------------------------
-conversion1
-conversion2
-conversion3 Action
+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
+
+gear Dx_gear <position> <Dx_gear> # [ft] x-offset from CG uiuc_aircraft.h
+gear Dy_gear <position> <Dy_gear> # [ft] y-offset from CG uiuc_aircraft.h
+gear Dz_gear <position> <Dz_gear> # [ft] z-offset from CG uiuc_aircraft.h
+gear cgear <position> <cgear> # [lb/ft/s] gear damping constant uiuc_aircraft.h
+gear kgear <position> <kgear> # [lb/ft] gear spring constant uiuc_aircraft.h
+gear muRoll <position> <muRoll> # [-] gear rolling friction coef uiuc_aircraft.h
+|gear strutLength <position> <sL> # [ft] gear strut length uiuc_aircraft.h
+
+================================GEAR POSITION================================
+
+There are 16 gear positions. Currently only the first three positions are
+rolling wheels. Position 1 is reserved for the nose wheel, position 2 is
+reserved for the right wheel, and position 3 is reserved for the left wheel.
+The rest of the positions can be left out or used to define locations on the
+plane such as the wing tips or tail. This way the wing tips or tail will not
+go "through" the ground but "bounce off" the ground.
+=============================================================================
+
ice iceTime <iceTime> # [s] time when icing begins uiuc_aircraft.h
-ice transientTime <tT> # [s] period for eta to reach eta_final uiuc_aircraft.h
-ice eta_final <eta_f> # [] icing severity factor 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_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 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 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_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 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
-record Dx_pilot # [ft] x-location ls_generic.h
-record Dy_pilot # [ft] y-loaction ls_generic.h
-record Dz_pilot # [ft] z-location ls_generic.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 V_north # [ft/s] x-velocity ls_generic.h
-record V_east # [ft/s] y-velocity ls_generic.h
-record V_down # [ft/s] z-velocity ls_generic.h
-record V_rel_wind # [ft/s] total velocity ls_generic.h
-record Dynamic_pressure # [lb/ft^2] dynamic pressure 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 Gamma # [rad] flight path angle ls_generic.h
-record P_body # [rad] roll rate ls_generic.h
-record Q_body # [rad] pitch rate ls_generic.h
-record R_body # [rad] yaw rate ls_generic.h
-record Phi # [rad] bank angle ls_generic.h
-record Theta # [rad] pitch attitude angle ls_generic.h
-record Theta_dot # [rad] rate change of theta ls_generic.h
-record Psi # [rad] heading angle ls_generic.h
-|record long_trim
-|record trim_inc
+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 Mass # [slug] aircraft mass ls_generic.h
-record Simtime # [s] current sim time global
-record dt # [s] current time step global
+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 Lat_control # [] roll input ls_cockpit.h
-record Rudder_pedal # [] yaw input ls_cockpit.h
-|record Throttle_pct # [%] throttle 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 Throttle[3] # [%] throttle deflection ls_cockpit.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 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 # [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_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
+
+fog fog_segments <fog_segments> # [-] number of fog points after this line
+fog fog_point <time> <intensity>
+
+Note: Between each fog_point there is a linear interpolation
+
+============================FOG EXAMPLE===============================
+
+fog fog_segments 4
+fog fog_point 30 500
+fog fog_point 35 200
+fog fog_point 40 -100
+fog fog_point 50 0
+
+The first line says that there will be 4 fog_point statements following.
+From time 0 to 30 seconds, the fog will increase linearly to 500. From
+30 to 35 seconds, the fog will decrease linearly to 200. From 35 to 40
+seconds the fog will decrease to -100. From 40 to 50 the fog will
+increase to 0.
+======================================================================
+
+
+# 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>
+
+
**********************************************************************
**********************************************************************
otherwise either the UIUC Aero Model or LaRCsim parts of the code will
probably crash.
-1) initial aircraft state (LaRCsim)
-Dx_pilot x-location [ft]
-Dy_pilot y-location [ft]
-Dz_pilot z-location [ft]
-
-(items below causing conflict with Flight Gear)
-|V_north x-velocity [ft/s]
-|V_east y-velocity [ft/s]
-|V_down z-velocity [ft/s]
-
-P_body roll rate [rad/s]
-Q_body pitch rate [rad/s]
-R_body yaw rate [rad/s]
-Phi bank angle [rad]
-Theta pitch attitude angle [rad]
-Psi heading angle [rad]
-
-2) aircraft geometry (UIUC Aero Model)
+1) aircraft geometry (UIUC Aero Model)
bw wingspan [ft]
cbar mean aerodynamic chord [ft]
Sw wing planform area [ft^2]
-3) engine properties (UIUC Engine Model)
+2) engine properties (UIUC Engine Model)
(some engine model must be specified, such as...)
engine simpleSingle
<or>
engine c172
-4) mass variables (LaRCsim)
+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]
-5) aerodynamic force/moment components (Aero Model)
+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 constant, as in CD=CDo+K*CL^2 []
+CDK induced drag constant []
<or>
CD_a d(CD)/d(alpha) [/rad]
Cmo pitch mom coef for all angles=0 []
Cl_beta d(Cl)/d(beta) [/rad]
Cn_beta d(Cn)/d(beta) [/rad]
-7) gear properties (none yet)
+5) gear properties
+(some gear properties must be defined otherwise the aircraft
+will not behave properly on the ground)
+Dx_gear x-offset from CG [ft]
+Dy_gear y-offset from CG [ft]
+Dz_gear z-offset from CG [ft]
+cgear gear damping constant [lb/ft/s]
+kgear gear spring constant [lb/ft]
+muGear gear rolling friction coef [-]
-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)
**********************************************************************
projects / flightgear.git / blobdiff