diff --git a/docs-mini/README.uiuc b/docs-mini/README.uiuc index da0c3ec48..bd6973b9b 100644 --- a/docs-mini/README.uiuc +++ b/docs-mini/README.uiuc @@ -2,10 +2,10 @@ * * * FGFS Reconfigurable Aircraft Flight Model * * Input File Documentation * -* Version 0.63, March 17, 2000 * +* Version 0.64, March 28, 2000 * * * * Authors: * -* Jeff Scott (jscott@uiuc.edu) * +* Jeff Scott (jscott@mail.com) * * Bipin Sehgal (bsehgal@uiuc.edu) * * Michael Selig (m-selig@uiuc.edu) * * Dept of Aero and Astro Engineering * @@ -15,14 +15,14 @@ * * ************************************************ - + ********************************************************************** 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. ********************************************************************** ********************************************************************** @@ -33,6 +33,7 @@ I. Conventions and Notations and Reading this Document: | 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 @@ -73,8 +74,8 @@ 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 +ice Icing model parameters +record Record desired quantites to file As each line of the input file is read, the code recognizes the keyword, enters the appropriate switch statement in the code, and @@ -103,7 +104,7 @@ 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 to be multiple by something +_ denotes stability derivative to be multiplied by something f "function of" (indicates an m*n matrix data table is given) 2) timing data (global simulator variables) @@ -140,7 +141,7 @@ M Mach number [] Re Reynolds number [] 4) atmosphere properties -Density air density [slug/ft^3] +Density air density [slug/ft^3] 5) geometric variables bw wingspan [ft] @@ -231,7 +232,7 @@ M_n_rp total yaw-moment [ft-lb] |muGear gear rolling friction coef [?] |strutLength gear strut length [ft] -12) icing model paramters +12) 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 [-] @@ -259,7 +260,7 @@ df flap deflection max maximum min minimum -(3) | (OPTIONAL DATA) +(3) | [OPTIONAL DATA] ===================== An input line may also be used to provide optional data that @@ -268,7 +269,7 @@ 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) +(4) # [COMMENTS] ================ Appended comments should be provided with each input line to indicate @@ -300,11 +301,11 @@ CD CDfCL # CD(CL), drag calculated in code based on CL ********************************************************************** ********************************************************************** -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 @@ -366,9 +367,15 @@ mass I_yy # [slug-ft^2] pitch inertia ls_gener mass I_zz # [slug-ft^2] yaw inertia ls_generic.h mass I_xz # [slug-ft^2] lateral cross inertia ls_generic.h -|engine thrust # [lb] max/min engine thrust uiuc_aircraft.h -engine simpleSingle # [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 + +# simple single engine maximum thrust [lb] uiuc_aircraft.h +engine simpleSingle + +engine c172 # use Cessna 172 engine model of Tony Peden + CL CLo # [] lift coef for all angles = 0 uiuc_aircraft.h CL CL_a # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h @@ -385,7 +392,8 @@ CL CLfade |CL CLfCT # CL(thrust coef) uiuc_aircraft.h |CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h |CL CL_afaM # 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 # [] drag coef for all angles = 0 uiuc_aircraft.h @@ -407,9 +415,11 @@ Cm Cm_q # [/rad] d(Cm)/d(q) uiuc_air Cm Cm_de # [/rad] d(Cm)/d(de) uiuc_aircraft.h |Cm Cmfa # [] Cm(alpha) uiuc_aircraft.h Cm Cmfade # [] Cm(alpha,delta_e) uiuc_aircraft.h + # Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h Cm Cmfade + CY CYo # [] side-force coef for all angles=0 uiuc_aircraft.h CY CY_beta # [/rad] d(CY)/d(beta) uiuc_aircraft.h CY CY_p # [/rad] d(CY)/d(p) uiuc_aircraft.h