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datcom3d_navion.m
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datcom3d_navion.m
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%*************************************************************************
% The source code contained herein was developed for Embry-Riddle
% Aeronautical University by Glenn P. Greiner, Professor and Jafar
% Mohammed, Student Assistant of the Aerospace Engineering Department,
% Daytona Beach Campus. Copyright 2008. All rights reserved.
% Although due care has been taken to present accurate programs this
% software is provided "as is" WITHOUT WARRANTY OF ANY KIND, EITHER
% EXPRESSED OR IMPLIED, AND EXPLICITLY EXCLUDING ANY IMPLIED WARRANTIES
% OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR USE. The entire risk as
% to the quality and performance of the software is with the user. The
% program is made available only for education and personal research. It
% may not be sold to other parties. If you copy some or all of the
% software you are requested to return a copy of any source additions that
% you believe make a significant improvement in its range of application.
%*************************************************************************
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% datcom3d NAVION Input File %
% March 24, 2008 %
% Works with Version datcom3d v1.2 %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
clear
clc
clf
%%% VISUALIZATION and RESOLUTION %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
wframe = 1; %0 = Shaded model
%1 = Wireframe model
fusres = 20; %Fuselage resolution
wgres = 20; %Wing,HT,VT resolution
%%% (DO NOT CHANGE VALUES IN THIS BOX) %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
XW=0;ZW=0;ALIW=0;XH=0;ZH=0;ALIH=0;XV=0;YV=0;numVT=1;VERTUP=1; %%
NX=0;X=zeros(20);S=zeros(20);R=zeros(20);ZU=zeros(20);ZL=zeros(20); %%
CHRDR_WG=0;CHRDBP_WG=0;CHRDTP_WG=0;SSPN_WG=0;SSPNOP_WG=0;SAVSI_WG=0; %%
SAVSO_WG=0;CHSTAT_WG=0;DHDADI_WG=0;DHDADO_WG=0;TC_WG=.12; %%
CHRDR_HT=0;CHRDBP_HT=0;CHRDTP_HT=0;SSPN_HT=0;SSPNOP_HT=0;SAVSI_HT=0; %%
SAVSO_HT=0;CHSTAT_HT=0;DHDADI_HT=0;DHDADO_HT=0;TC_HT=.12; %%
CHRDR_VT=0;CHRDBP_VT=0;CHRDTP_VT=0;SSPN_VT=0;SSPNOP_VT=0;SAVSI_VT=0; %%
SAVSO_VT=0;CHSTAT_VT=0;TC_VT=.12; %%
SPANFI_F=0;SPANFO_F=0;CHRDFI_F=0;CHRDFO_F=0;DELTA_F=0; %%
SPANFI_A=0;SPANFO_A=0;CHRDFI_A=0;CHRDFO_A=0;DELTAL_A=0;DELTAR_A=0; %%
SPANFI_E=0;SPANFO_E=0;CHRDFI_E=0;CHRDFO_E=0;DELTA_E=0; %%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%% INPUT PARAMETERS BELOW %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% SYNTHS parameters
XW = 5.80;
ZW = -2.12;
ALIW = 0.0;
XH = 21.64;
ZH = 0.5;
ALIH = 0.0;
XV = 23.21;
ZV = 0.0;
% BODY parameters
NX = 18;
X = [0.0,0.314,0.666,2.352,4.077,5.449,6.115,6.939,7.644,8.311,9.840,...
11.055,12.505,14.191,17.327,20.503,23.639,27.755];
ZU = [1.019,1.372,1.490,1.764,2.038,2.078,2.509,2.979,3.136,3.215,...
3.136,2.900,2.470,1.686,1.450,1.215,0.862,0.548];
ZL = [-1.019,-1.372,-1.490,-1.764,-2.038,-2.117,-2.156,-2.195,-2.195,...
-2.195,-2.195,-2.156,-2.117,-1.960,-1.568,-1.176,-0.862,-0.392];
R = [1.176,1.490,1.568,1.803,1.999,2.097,2.156,2.176,2.215,2.215,2.195,...
2.156,2.078,1.901,1.470,1.039,0.627,0.078];
S = [3.765,6.422,7.433,9.992,12.799,13.815,15.802,17.685,18.552,...
18.823,18.384,17.130,14.969,10.887,6.881,3.904,2.163,0.125];
% WING parameters
CHRDTP_WG = 3.73;
SSPNE_WG = 14.43;
SSPN_WG = 16.7;
CHRDR_WG = 7.29;
SAVSI_WG = 0.0;
CHSTAT_WG = .25;
TWISTA_WG = 0.0;
DHDADI_WG = 8.5;
DHDADO_WG = 0.0;
TC_WG = .18;
% HORIZONTAL TAIL parameters
CHRDTP_HT = 2.51;
SSPNE_HT = 6.19;
SSPN_HT = 6.59;
CHRDR_HT = 5.02;
SAVSI_HT = 6.0;
CHSTAT_HT = 0.25;
TWISTA_HT = 0.0;
DHDADI_HT = 0.0;
DHDADO_HT = 0.0;
% VERTICAL TAIL parameters
CHRDTP_VT = 1.88;
SSPNE_VT = 4.39;
SSPN_VT = 5.02;
CHRDR_VT = 4.47;
SAVSI_VT = 13.5;
CHSTAT_VT = .25;
% WING FLAP
% $SYMFLP FTYPE=1.0,NDELTA=4.0,
% DELTA(1)=0.,-10.,-15.,-20.,
% SPANFI=2.2,SPANFO=11.0,CHRDFI=1.5,CHRDFO=1.0,NTYPE=1.0,
% CB=.357,TC=.220,PHETE=.003,PHETEP=.002$
SPANFI_F=2.2;
SPANFO_F=11;
CHRDFI_F=1.5;
CHRDFO_F=1;
DELTA_F=30;
% WING AILERON
% $ASYFLP STYPE=4.0,NDELTA=9.0,
% DELTAL(1)=20.,15.,10.,5.,0.,-5.,-10.,-15.,-20.,
% DELTAR(1)=-20.,-15.,-10.,-5.,0.,5.,10.,15.,20.,
% SPANFI=11.0,SPANFO=16.7,CHRDFI=1.0,CHRDFO=.6$
SPANFI_A=11;
SPANFO_A=16.7;
CHRDFI_A=1;
CHRDFO_A=.6;
DELTAL_A=-20;
DELTAR_A=20;
% ELEVATOR
% $SYMFLP FTYPE=1.0,NDELTA=9.0,DELTA(1)=-40.,-30.,-20.,-10.,0.,10.,20.,30.,
% 40.,SPANFI=.700,SPANFO=6.586,CHRDFI=1.882,CHRDFO=.706,NTYPE=1.0,
% CB=.357,TC=.220,PHETE=.003,PHETEP=.002$
SPANFI_E=.7;
SPANFO_E=6.586;
CHRDFI_E=1.882;
CHRDFO_E=.706;
DELTA_E=10;
%%% PLOTTING %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
warning off MATLAB:divideByZero
hold on
plotFuselage(NX,X,S,R,ZU,ZL,fusres)
plotWing(XW,ZW,ALIW,CHRDR_WG,CHRDBP_WG,CHRDTP_WG,SSPN_WG,SSPNOP_WG,SAVSI_WG,SAVSO_WG,CHSTAT_WG,DHDADI_WG,DHDADO_WG,...
SPANFI_F,SPANFO_F,CHRDFI_F,CHRDFO_F,DELTA_F,SPANFI_A,SPANFO_A,CHRDFI_A,CHRDFO_A,DELTAL_A,DELTAR_A,TC_WG,wgres)
plotHT(XH,ZH,ALIH,CHRDR_HT,CHRDBP_HT,CHRDTP_HT,SSPN_HT,SSPNOP_HT,SAVSI_HT,SAVSO_HT,CHSTAT_HT,DHDADI_HT,DHDADO_HT,...
SPANFI_E,SPANFO_E,CHRDFI_E,CHRDFO_E,DELTA_E,TC_HT,wgres)
plotVT(XV,YV,ZV,CHRDR_VT,CHRDBP_VT,CHRDTP_VT,SSPN_VT,SSPNOP_VT,SAVSI_VT,SAVSO_VT,CHSTAT_VT,VERTUP,TC_VT,wgres)
%%% VIEWPORT/FIGURE PROPERTIES %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
if wframe == 0
%colormap([1 .7 .1]) %Set a/c to gold
colormap([0 0 1]) %Set a/c to blue
shading interp %Interpolated shading
lighting gouraud %Smooth airplane mesh
%camlight right %Apply a light source
%Custom Lighting Options, Note:[X Y Z]
light('Position',[1 -2 1],'Style','infinite');
light('Position',[1 2 1],'Style','infinite');
light('Position',[0 0 -6],'Style','infinite');
else
colormap([1 1 1]) %Set a/c to white
end
axis off %Turn off axis
axis equal %Correct aspect ratio
camva(4.5) %Zoom in a/c to fit figure
view(3) %Apply initial viewport rotation
%camproj('perspective') %Perspective viewing (not R2006a compatible)
rotate3d on %Rotate icon enabled at start up
%showplottool('plotbrowser')
set(gcf,'NumberTitle','off','Name','Aircraft Plot','Color',[1 1 1]);