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clDefaults.m
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clDefaults.m
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% A static class containing the parameters used in the Aircraft Analyzer
% All numbers below are in metric units (kg, N, m, s, etc.)
% Convention dictates angles should be in deg
classdef clDefaults
properties (Constant, GetAccess=public)
g = 9.81;
%------------------------------
% Atmospheric Data
%------------------------------
Air_runway_alt = 0;
Air_cruise_height = 50;
Air_DISA = 0;
Air_cruise_speed = 18;
Air_CD0 = 0.17;
Air_CL_max = 1.73;
Air_mu = 1.81e-5;
%-------------------------------
% Propulsion
%-------------------------------
Propulsion_type = 1;
Propulsion_thrust = '50-0.6*V';
Propulsion_consumption = '0';
Propulsion_total_fuel = '1000';
Propulsion_thrust_line = [0; 0; 0];
%-------------------------------
% Interactions
%-------------------------------
Interaction_rotation_alpha = 8; % max linear CL-alpha
Interaction_flare_alpha = 8;
Interaction_mu_tire = 0.015;
Interaction_mu_brake = 0.5;
Interaction_max_elev = 20;
Interaction_max_ail = 20;
Interaction_max_rud = 20;
Interaction_servo_resolution = 60/128;
%-------------------------------
% Inertia
%-------------------------------
Inertia_total_mass = 10;
Inertia_CGx = 0.09;
Inertia_CGy = 0;
Inertia_CGz = 0;
%-------------------------------
% Geometry
%-------------------------------
Geometry_MLG_height = 0.25;
Geometry_MLG_width = 0.39
Geometry_MLG_X = 0.19
Geometry_NG_height = 0.25
Geometry_NG_X = -0.26
Geometry_wing_duplicate = 1;
Geometry_wing_translate = [0; 0; 0];
Geometry_hstab_duplicate = 1;
Geometry_hstab_translate = [0; 0; 0];
Geometry_vstab_duplicate = 0;
Geometry_vstab_translate = [0; 0; 0];
Geometry_fuselage_duplicate = 0;
Geometry_fuselage_translate = [0; 0; 0];
Geometry_fuselage_file = '';
end
end