Updates.
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* *
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* FGFS Reconfigurable Aircraft Flight Model *
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* Input File Documentation *
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* Version 0.63, March 17, 2000 *
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* Version 0.64, March 28, 2000 *
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* *
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* Authors: *
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* Jeff Scott (jscott@uiuc.edu) *
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* Jeff Scott (jscott@mail.com) *
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* Bipin Sehgal (bsehgal@uiuc.edu) *
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* Michael Selig (m-selig@uiuc.edu) *
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* Dept of Aero and Astro Engineering *
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@ -15,14 +15,14 @@
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* *
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************************************************
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**********************************************************************
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This documentation includes:
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- Required and optional input lines.
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- Input line formats and conventions.
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Viewing this file in emacs makefile-mode with color makes this file
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easier to read.
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Viewing this file in emacs makefile-mode with color makes this file
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easier to read.
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**********************************************************************
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**********************************************************************
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@ -33,6 +33,7 @@ I. Conventions and Notations and Reading this Document:
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| Optional data
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| Sometimes indicates a feature not yet used,
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but proposed convention is indicated nevertheless.
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<...> Value or file name to be placed here
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|| Input line disabled
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|| Option disabled
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... Repeat similar data
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@ -73,8 +74,8 @@ CY Aerodynamic y-force quantities (lateral)
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Cl Aerodynamic l-moment quantities (lateral)
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Cn Aerodynamic n-moment quantities (lateral)
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|gear Landing gear model quantities
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ice Aircraft icing model parameters
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record Record desired quantities to the file: uiuc_record.dat
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ice Icing model parameters
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record Record desired quantites to file
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As each line of the input file is read, the code recognizes the
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keyword, enters the appropriate switch statement in the code, and
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@ -103,7 +104,7 @@ The conventions used for naming the variables are provided below.
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Several of these variable names are not currently used.
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1) variable class
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_ denotes stability derivative to be multiple by something
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_ denotes stability derivative to be multiplied by something
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f "function of" (indicates an m*n matrix data table is given)
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2) timing data (global simulator variables)
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@ -140,7 +141,7 @@ M Mach number []
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Re Reynolds number []
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4) atmosphere properties
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Density air density [slug/ft^3]
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Density air density [slug/ft^3]
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5) geometric variables
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bw wingspan [ft]
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@ -231,7 +232,7 @@ M_n_rp total yaw-moment [ft-lb]
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|muGear gear rolling friction coef [?]
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|strutLength gear strut length [ft]
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12) icing model paramters
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12) icing model parameters
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iceTime time when icing begins [s]
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transientTime time period over which eta increases to final [s]
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eta_final icing severity factor at end of transient time [-]
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@ -259,7 +260,7 @@ df flap deflection
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max maximum
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min minimum
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(3) | (OPTIONAL DATA)
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(3) | [OPTIONAL DATA]
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=====================
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An input line may also be used to provide optional data that
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@ -268,7 +269,7 @@ operate. As with the variable data described in section (2), multiple
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values or data files may be provided if the code is written to use
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them.
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(4) # (COMMENTS)
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(4) # [COMMENTS]
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================
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Appended comments should be provided with each input line to indicate
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@ -300,11 +301,11 @@ CD CDfCL # CD(CL), drag calculated in code based on CL
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**********************************************************************
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**********************************************************************
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IV. Definitions of Input Lines Currently Available:
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IV. Input Line Definitions:
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Of all the possible permutation of variable names described above in
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section II, only some are currently implemented in the code. These
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are described below. Comments, denoted by '#,' are used to define the
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Of all the possible permutations of variable names described above in
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section II, only some are curently implemented in the code. These are
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described below. Comments, denoted by '#,' are used to define the
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lines and to indicate examples of the data if additional clarity is
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needed for unique situations. Again, those lines beginning with '|'
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are not currently implemented in the code, but indicate planned
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@ -366,9 +367,15 @@ mass I_yy <I_yy> # [slug-ft^2] pitch inertia ls_gener
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mass I_zz <I_zz> # [slug-ft^2] yaw inertia ls_generic.h
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mass I_xz <I_xz> # [slug-ft^2] lateral cross inertia ls_generic.h
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|engine thrust <thrustMax> <thrustMin> # [lb] max/min engine thrust uiuc_aircraft.h
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engine simpleSingle <sSMaxThrust> # [lb] simple single engine uiuc_aircraft.h
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engine c172 # use Cessna 172 engine model of Tony Peden
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# maximum and minimum engine thrust [lb] uiuc_aircraft.h
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|engine thrust <thrustMax> <thrustMin>
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# simple single engine maximum thrust [lb] uiuc_aircraft.h
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engine simpleSingle <simpleSingleMaxThrust>
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engine c172 # use Cessna 172 engine model of Tony Peden
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CL CLo <CLo> # [] lift coef for all angles = 0 uiuc_aircraft.h
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CL CL_a <CL_a> # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h
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@ -385,7 +392,8 @@ CL CLfade <CLfade.dat> <conversion1> <conversion2> <conversion3>
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|CL CLfCT <CLfCT.dat> # CL(thrust coef) uiuc_aircraft.h
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|CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h
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|CL CL_afaM <CL_afaM.dat> # CL_alpha(alpha,Mach #) uiuc_aircraft.h
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# there are examples that might later be included in the code
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# these are sample examples that might be used in later versions of the code
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# note that CD terms must come after CL for induced drag to be computed
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CD CDo <CDo> # [] drag coef for all angles = 0 uiuc_aircraft.h
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@ -407,9 +415,11 @@ Cm Cm_q <Cm_q> # [/rad] d(Cm)/d(q) uiuc_air
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Cm Cm_de <Cm_de> # [/rad] d(Cm)/d(de) uiuc_aircraft.h
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|Cm Cmfa <Cmfa.dat> # [] Cm(alpha) uiuc_aircraft.h
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Cm Cmfade <Cmfade.dat> # [] Cm(alpha,delta_e) uiuc_aircraft.h
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# Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h
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Cm Cmfade <Cmfade.dat> <conversion1> <conversion2> <conversion3>
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CY CYo <CYo> # [] side-force coef for all angles=0 uiuc_aircraft.h
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CY CY_beta <CY_beta> # [/rad] d(CY)/d(beta) uiuc_aircraft.h
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CY CY_p <CY_p> # [/rad] d(CY)/d(p) uiuc_aircraft.h
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