% read datcom data
clear all
close all
clc
%%

load navion_data2
%load citation_data2

%data{1} = data{3};

%% Geometry
cref = data{1}.cbar*0.3048; % reference length - ft to m conversion
sref = data{1}.sref*0.3048^2; % reference area - ft to m conversion
b = 2*data{1}.wsspn*0.3048; % wing span - ft to m conversion

xcg = [data{1}.xcg_b, 0, data{1}.zcg_b]*0.3048;
xcp = [-interp1(data{1}.alpha, data{1}.xcp, 0.0)*cref+xcg(1), 0, 0];
%xcp = [-0.4+xcg(1), 0, 0];

theta_0 = 0.0;
h = data{1}.alt*0.3048; % altitude / height

g = 9.81;

% Navion
m = 1260;

Ixx = 1420;
Iyy = 4422.0;
Izz = 4786.0; 
Ixz = 0.0;

I_tensor = [Ixx 0 -Ixz; 0 Iyy 0; -Ixz 0 Izz];

u0 = 55.4;


% Citation
%m = 3175;
%Iyy = 7422.0;
%u0 = 334.4*0.4;



%% Aerodynamics
alpha = data{1}.alpha'; % angles of attack
cl = data{1}.cl; % lift coefficient
cd = data{1}.cd; % drag coefficient
cm = data{1}.cm; % pitching moment coefficient

cmq = data{1}.cmq(1);
clad = data{1}.clad;
cmad = data{1}.cmad;

% lateral data
cyb = data{1}.cyb(1);
cyp = data{1}.cyp;
cnp = data{1}.cnp;
cnr = data{1}.cnr;
cnb = data{1}.cnb(1);
clb = data{1}.clb;
clr = data{1}.clr;
clq = data{1}.clq(1);
clp = data{1}.clp;

deltae = data{1}.delta'; % elevatointerp1(alpha, cd, u(1))r/flap deflection angles
dcldeltae = data{1}.dcl_sym; % lift coefficient increment due to elevator/flap deflection
dcmdeltae = data{1}.dcm_sym; % pitching moment coefficient increment due to elevator/flap deflection
dcdmindeltae = data{1}.dcdmin_sym;  % drag coefficient (parasite) increment due to elevator/flap deflection
dcdideltae = data{1}.dcdi_sym;   % drag coefficient (induced) increment due to elevator/flap deflection

deltaa = data{1}.deltar;
clroll = data{1}.clroll;
cn_asy = data{1}.cn_asy;