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fLattice_setup2.m
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function [lattice,ref]=fLattice_setup2(geo,state,latticetype)
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Copyright (C) 1999, 2007 Tomas Melin
%
% This file is part of Tornado
%
% Tornado is free software; you can redistribute it and/or
% modify it under the terms of the GNU General Public
% License as published by the Free Software Foundation;
% either version 2, or (at your option) any later version.
%
% Tornado is distributed in the hope that it will be useful,
% but WITHOUT ANY WARRANTY; without even the implied
% warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR
% PURPOSE. See the GNU General Public License for more
% details.
%
% You should have received a copy of the GNU General Public
% License along with Tornado; see the file GNU GENERAL
% PUBLIC LICENSE.TXT. If not, write to the Free Software
% Foundation, 59 Temple Place -Suite 330, Boston, MA
% 02111-1307, USA.
%
% usage: [LATTICE,REF]=fLattice_setup(GEO,STATE,latticetype);
%
% Generates the LATTICE and REF structs from the GEO and STATE structs.
% First, the function invokes geosetup to yield the data correlation to
% the geometry, then it appends wake data (i.e. the deflecting wake) in
% wakesetup, and lastly it rotates any control surface points in the
% lattice struct.
%
% If latticetype=1, the lattice produced will be a standard vortex
% lattice -lattice, i.e. only horseshoes, not slings.
%
% Example:
%
% [lattice,ref]=fLattice_setup(geo,state);
%
% Calls:
% geosetup15 Assembles the lattice and ref structured from geo
% wakesetup2 Adds the wake to the lattice struct.
% setrudder3 Deflects any flap, aileron, elevator or ruder.
% All three functions above are inline as only this
% function calls them.
% terror Displays various Error messages.
%
% Author: Tomas Melin <melin@kth.se>
% Keywords: lattice generation
%
% Revision History:
% Bristol, 2007-06-27: Addition of new header. TM
% Spånga, 2021-09-19: Updated to MATLAB R2020, TM
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
try
latticetype;
catch
latticetype=0; %If latticetype is unspecified, go with vortexslings.
end
%warning('off')
[lattice,ref]=geosetup15(geo);
%Aircraft lattice done
[dim1 dim2 dim3]=size(lattice.VORTEX);
if dim2==8 %checking if vortex has wake
lattice.VORTEX=lattice.VORTEX(:,2:7,:); %discarding far wake points in wake.
end
if state.AS~=0 %appending wake lattice points (farpoints)
lattice=wakesetup2(lattice,state,ref); %setting up wake legs.
%disp(' ')
%disp('*** Lattice created. ***')
%disp(' ')
stat=1;
else
terror(13)
end
[n,m]=find(geo.flapped');
if isempty(m) %Does any flaps have rudder deflections?
else
noof_flaps=sum(sum(geo.flapped));
for k=1:noof_flaps %Loop all flaps and set them according to setting vector
flap_no=k;
deflection=(geo.flap_vector(m(k),n(k)));
[lattice]=setrudder3(flap_no,deflection,lattice,geo);
end
end
%% Allmoving surface setting here
for tx=1:geo.nwing;
if geo.allmove(tx)==0;
%Not an allmovning wing
else
deflection=(geo.allmove_def(tx));
[lattice]=wingrotation_allmove(tx,geo,lattice,geo.allmove_axis(tx,:),geo.allmove_origin(tx,:),deflection,geo.allmove_symetric(tx,:));
end
end
%% End allmoving surface
[dim1 dim2 dim3]=size(lattice.VORTEX);
%STANDARD VLM, REPLACING SLINGS WITH HORSESHOES.
if latticetype==1
%tdisp('Standard VLM')
if dim2==8
temporary=lattice.VORTEX(:,[1 4 5 8],:); %changing lattice to a standard VLM
else
temporary=lattice.VORTEX(:,[1 3 4 6],:); %if there is no wake
end
temporary(:,1,3)=temporary(:,2,3); %Flattening wake
temporary(:,4,3)=temporary(:,3,3); %Flattening wake
lattice.VORTEX=temporary;
end
%% Adding propeller field
if isfield(geo,'prop')
lattice.prop=propmain(geo,state);
end
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%Inline function geosetup
function [lattice,ref]=geosetup15(geo)
void=0;
try
geo.meshtype;
catch
geo.meshtype=ones(size(geo.T));
end
%npan=sum(sum((geo.nx+geo.fnx).*geo.ny,2).*(geo.symetric+1)');%number of panels
lattice.COLLOC=[];%zeros(npan,3); %initializing
lattice.VORTEX=[];%zeros(npan,3);
lattice.N=[];%zeros(npan,8,3);
lattice.XYZ=[];%zeros(npan,5,3);
X=[];
Y=[];
Z=[];
S=1;
Cmac=0;
CHORDS=[];
loopsperwing=geo.nelem;
noofloops=loopsperwing;
temp=0;
noofwings=size(loopsperwing');
for s=1:noofwings %Intermediate variable setuploop
CHORDS(s,1)=geo.c(s); %calculating chords of first element
SX(s,1)=geo.startx(s); %Element apex calculation
SY(s,1)=geo.starty(s); % Same-o
SZ(s,1)=geo.startz(s); % Same-o
end
t=0; %resetting ticker variable
for s=1:noofwings
for t=1:(noofloops(s))
%Chord loop, generating chords for wing sections.
%And startingpoints for partition-quads
CHORDS(s,t+1)=CHORDS(s,t)*geo.T(s,t); %calculating
%element root-chord
SX(s,t+1)=0.25*CHORDS(s,t)+geo.b(s,t)*(tan(geo.SW(s,t)))...
-0.25*CHORDS(s,t+1)+SX(s,t) ;
SY(s,t+1)=geo.b(s,t)*cos(geo.dihed(s,t))+SY(s,t);
SZ(s,t+1)=geo.b(s,t)*sin(geo.dihed(s,t))+SZ(s,t);
end
end
%MAIN GEOMETRY SETUP LOOP, CREATES Partition QUAD PANELS, VORTICIES AND COLL-POINTS
for s=1:noofwings
for t=1:noofloops(s) %setuploop
[C V N2 P]=geometry19(geo.fnx(s,t),geo.ny(s,t),geo.nx(s,t),...
geo.fsym(s,t),geo.fc(s,t),geo.flapped(s,t),geo.TW(s,t,:),geo.foil(s,t,:),...
geo.T(s,t),geo.SW(s,t),CHORDS(s,t),geo.dihed(s,t),geo.b(s,t),...
geo.symetric(s),SX(s,t),SY(s,t),SZ(s,t),geo.meshtype(s,t));
lattice.COLLOC=[lattice.COLLOC;C];
lattice.VORTEX=[lattice.VORTEX;V];
lattice.N=[lattice.N;N2];
S(s,t)=geo.b(s,t)*CHORDS(s,t)*((1+geo.T(s,t)))/2;
Cmgc(s,t)=S(s,t)/geo.b(s,t);
if geo.symetric(s)==1
S(s,t)=S(s,t)*2;
end
lattice.XYZ=[lattice.XYZ;P];
end
end
ref.b_ref=config('b_ref');
if isempty(ref.b_ref)
B=sum(geo.b,2);
ref.b_ref=B(1); %reference span = half-span of first wing
ref.b_ref=ref.b_ref*(geo.symetric(1)+1);
end
ref.S_ref=config('S_ref');
if isempty(ref.S_ref)
S_r=sum(S,2);
ref.S_ref=S_r(1); %reference area = area of first wing
end
C_m=sum(Cmgc.*S,2);
ref.C_mgc=C_m(1)/ref.S_ref; %Mean Geometric Chord Gross surface Main (first)
ref.C_mac=config('C_mac');
if isempty(ref.C_mac)
[ref.C_mac void]=fCmac(CHORDS(1,:),geo.b(1,:),geo.SW(1,:),...
SX(1,:),SY(1,:),SZ(1,:),geo.dihed(1,:),geo.symetric(1)); %Main (first) wing Mean aerodymaic chord calculation
end
ref.mac_pos=config('mac_pos');
if isempty(ref.mac_pos)
[void ref.mac_pos]=fCmac(CHORDS(1,:),geo.b(1,:),geo.SW(1,:),...
SX(1,:),SY(1,:),SZ(1,:),geo.dihed(1,:),geo.symetric(1)); %Main (first) wing Mean aerodymaic chord calculation
%mac_pos=-mac_pos
end
lock(1)=0; %Unlock geometry loaded bit
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%55
function [lattice]=wakesetup2(lattice,state,ref)
infdist=config('infinity');
if isempty(infdist)
infdist=6*ref.b_ref;
end
[a b c]=size(lattice.VORTEX);
V2=lattice.VORTEX;
c=[1 b];
infx=infdist*cos(state.alpha)*cos(state.betha);
infy=-infdist*sin(state.betha);
infz=infdist*sin(state.alpha)*cos(state.betha);
for t=1:a
for s=1:2
x=infx+lattice.VORTEX(t,c(s),1);
y=infy+lattice.VORTEX(t,c(s),2);
z=infz+lattice.VORTEX(t,c(s),3);
psi=state.P/state.AS*x;
theta=state.Q/state.AS*x;
fi=state.R/state.AS*x;
dx(t,s)=-x*(2-cos(theta)-cos(fi));
dy(t,s)=+sin(psi)*z-sin(fi)*x+(1-cos(psi))*y;
dz(t,s)=sin(theta)*x-sin(psi)*y+(1-cos(psi))*z;
end
end
for i=1:a
INF1(i,1,1)=lattice.VORTEX(i,1,1)+infx+dx(i,1);
INF1(i,1,2)=lattice.VORTEX(i,1,2)+infy+dy(i,1);
INF1(i,1,3)=lattice.VORTEX(i,1,3)+infz+dz(i,1);
INF2(i,1,1)=lattice.VORTEX(i,b,1)+infx+dx(i,2);
INF2(i,1,2)=lattice.VORTEX(i,b,2)+infy+dy(i,2);
INF2(i,1,3)=lattice.VORTEX(i,b,3)+infz+dz(i,2);
end
lattice.VORTEX=[INF1(:,1,:) V2(:,:,:) INF2(:,1,:)];
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function [lattice]=setrudder3(rudder,deflection,lattice,geo)
[I K]=find(geo.flapped');
try
wing=K(rudder);
division=I(rudder);
catch
terror(2)
return
end
[q1 q2 q3]=size(lattice.VORTEX);
if q2==8
tempV1=lattice.VORTEX(:,1,:);
tempV2=lattice.VORTEX(:,8,:);
lattice.VORTEX=lattice.VORTEX(:,2:7,:);
end
fsym=geo.fsym(wing,division);
mp=3;
t=1;
r=0;
[q6 q7]=size(geo.nx);
nr=((geo.nx+geo.fnx).*geo.ny).*((ones(q6,q7)+(geo.symetric'*ones(1,q7))));
[q4 q5]=size(nr);
for i=1:q4
for j=1:q5
if geo.flapped(i,j)==1
r=r+1;
end
if r<rudder
t=t+nr(i,j);
end
end
end
nx=geo.nx(wing,division);
ny=geo.ny(wing,division);
fnx=geo.fnx(wing,division);
a1=[lattice.XYZ(t+nx,1,1) lattice.XYZ(t+nx,1,2) lattice.XYZ(t+nx,1,3)];
b1=[lattice.XYZ(t+nx,2,1) lattice.XYZ(t+nx,2,2) lattice.XYZ(t+nx,2,3)];
a2=[lattice.XYZ(t+nx,2,1) -lattice.XYZ(t+nx,2,2) lattice.XYZ(t+nx,2,3)];
b2=[lattice.XYZ(t+nx,1,1) -lattice.XYZ(t+nx,1,2) lattice.XYZ(t+nx,1,3)];
h=b1-a1; %defining hingeline SB-side
h1_hat=h./norm(h); %normalizing hingeline
h2=b2-a2; %defining hingeline P-side
h2_hat=h2./norm(h2); %normalizing hingeline
s=nx+fnx;
for i=1:(nx+fnx)*ny*(1+geo.symetric(wing));
%loop for trailing edge points
rad2=t+i-1;
if rad2 < t+(nx+fnx)*ny; %if wing is symmetric and
%panel is on the SB-side
a=a1;
b=b1;
h_hat=h1_hat;
def=deflection;
else % if wing is on the P-side
h_hat=h2_hat;
a=a2;
b=b2;
if fsym==0; %if flap deflection is anti-
%symmetric
def=-deflection;
else
def=deflection;
end
end
for col=1:5:6
p1(1)=lattice.VORTEX(rad2,col,1);
p1(2)=lattice.VORTEX(rad2,col,2);
p1(3)=lattice.VORTEX(rad2,col,3);
if col<=mp
r=p1-a;
p2=trot3(h_hat,r,def);
lattice.VORTEX(rad2,col,1)=p2(1)+a(1);
lattice.VORTEX(rad2,col,2)=p2(2)+a(2);
lattice.VORTEX(rad2,col,3)=p2(3)+a(3);
else
r=p1-b;
p2=trot3(h_hat,r,def);
lattice.VORTEX(rad2,col,1)=p2(1)+b(1);
lattice.VORTEX(rad2,col,2)=p2(2)+b(2);
lattice.VORTEX(rad2,col,3)=p2(3)+b(3);
end
end
end
for i=s:s:s*ny*(1+geo.symetric(wing))
%stepping through number of strips
for j=0:fnx-1 %stepping through number of flappanels
ii=i-fnx;
rad1=(t+ii+j);
if rad1 < t+(nx+fnx)*ny; %if wing is symmetric and
%panel is on the SB-side
a=a1;
b=b1;
h_hat=h1_hat;
def=deflection;
else % if wing is on the P-side
h_hat=h2_hat;
a=a2;
b=b2;
if fsym==0; %if flap deflection is anti-
%symmetric
def=-deflection;
else
def=deflection;
end
end
for k=0:3 %Vortex loop
col=(k+mp-1);
p1(1)=lattice.VORTEX(rad1,col,1);
p1(2)=lattice.VORTEX(rad1,col,2);
p1(3)=lattice.VORTEX(rad1,col,3);
if col<=mp
r=p1-a;
p2=trot3(h_hat,r,def);
lattice.VORTEX(rad1,col,1)=p2(1)+a(1);
lattice.VORTEX(rad1,col,2)=p2(2)+a(2);
lattice.VORTEX(rad1,col,3)=p2(3)+a(3);
else
r=p1-b;
p2=trot3(h_hat,r,def);
lattice.VORTEX(rad1,col,1)=p2(1)+b(1);
lattice.VORTEX(rad1,col,2)=p2(2)+b(2);
lattice.VORTEX(rad1,col,3)=p2(3)+b(3);
end
end
%collocarion point rotation
p1(1)=lattice.COLLOC(rad1,1);
p1(2)=lattice.COLLOC(rad1,2);
p1(3)=lattice.COLLOC(rad1,3);
c=(a+b)./2;
r=p1-c;
p2=trot3(h_hat,r,def);
lattice.COLLOC(rad1,1)=p2(1)+c(1);
lattice.COLLOC(rad1,2)=p2(2)+c(2);
lattice.COLLOC(rad1,3)=p2(3)+c(3);
%Normals rotation
p1(1)=lattice.N(rad1,1);
p1(2)=lattice.N(rad1,2);
p1(3)=lattice.N(rad1,3);
c=(a+b)./2;
r=p1;
p2=trot3(h_hat,r,def);
lattice.N(rad1,1)=p2(1);
lattice.N(rad1,2)=p2(2);
lattice.N(rad1,3)=p2(3);
for k=0:4 %panelcoords
col=(k+1);
p1(1)=lattice.XYZ(rad1,col,1);
p1(2)=lattice.XYZ(rad1,col,2);
p1(3)=lattice.XYZ(rad1,col,3);
%disp('************')
if col<=1;
r=p1-a;
p2=trot3(h_hat,r,def);
lattice.XYZ(rad1,col,1)=p2(1)+a(1);
lattice.XYZ(rad1,col,2)=p2(2)+a(2);
lattice.XYZ(rad1,col,3)=p2(3)+a(3);
elseif col<=3
r=p1-b;
p2=trot3(h_hat,r,def);
lattice.XYZ(rad1,col,1)=p2(1)+b(1);
lattice.XYZ(rad1,col,2)=p2(2)+b(2);
lattice.XYZ(rad1,col,3)=p2(3)+b(3);
else
r=p1-a;
p2=trot3(h_hat,r,def);
lattice.XYZ(rad1,col,1)=p2(1)+a(1);
lattice.XYZ(rad1,col,2)=p2(2)+a(2);
lattice.XYZ(rad1,col,3)=p2(3)+a(3);
end
end
end
end
if q2==8
lattice.VORTEX=[tempV1 lattice.VORTEX tempV2];
end
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function [C_mac,mac_start_coo]=fCmac(C,b,SW,sx,sy,sz,dihed,sym)
[void noofpan]=size(C); %Create counter
for i=1:noofpan-1;
T(i)=C(i+1)/C(i); %partition taper
Cb=C(i); %Base chord
Ct=C(i+1); %Tip chord
b_mac(i)=b(i)*(2*Ct+Cb)/(3*(Ct+Cb)); %Tp pos
Cmac(i)=Cb-(Cb-Ct)/b(i)*b_mac(i); %Chord at tp pos
Cmac(find(isnan(Cmac)))=0; %if the first wing has fewer paertitions
start(i,1)=0.25*Cb+b_mac(i)*tan(SW(i))-0.25*Cmac(i)+sx(i); %Mac start x position
start(i,2)=cos(dihed(i))*b_mac(i)+sy(i);
start(i,3)=sin(dihed(i))*b_mac(i)+sz(i);
end
if sym
start(:,2)=0;
end
A=(1+T).*C(1:end-1).*b./2; %Area of partitions
C_mac=sum(Cmac.*A)./sum(A); % Area weighing for multiple
mac_start_coo(1)=sum((start(:,1).*A')./sum(A)); % partition wing
mac_start_coo(2)=sum((start(:,2).*A')./sum(A));
mac_start_coo(3)=sum((start(:,3).*A')./sum(A)); % partition wing% partition wing
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function [C,Vor,N,P]=...
geometry19(fnx,ny,nx,fsym,fc,flapped,TW,foil...
,T,SW,c,dihed,b,sym,sx,sy,sz,meshtype)
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% GEOMETRY: Essential function for TORNADO %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Determines the position of vortex-collocation-normals %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Author: Tomas Melin, KTH, Division of Aeronautics %
% copyright 2000 %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% CONTEXT: Subsidary function for TORNADO %
% Called by: setup %
% Calls: MATLAB 5.2 std fcns, tmesh, drawhinge%
% slope, normals %
% Loads: none %
% Saves: none %
% Input: wing and division number %
% Output:coordinades for collocationpoints, vorticies and%
% Normals %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
TEP=[];
TEP1=[];
TEP2=[];
INF=[];
INF1=[];
INF2=[];
ox=sx;
oy=sy;
oz=sz;
neqns=(nx+fnx)*ny;
dx=(c*(1-fc)/nx);
if flapped==1
fdx=(c*fc/fnx);
else
fdx=0;
end
a1=ones(nx,1)*dx;
a2=ones(fnx,1)*fdx;
dr=[a1' a2'];
%%%%%%%%%%%%%%%%%%%%%%%
%Calculates geometry, collocationpoints
%panels and vortecies for a flat quad
%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%
% Plotting planform
%%%%%%%%%%%%%%%%%%
lem(1)=0.25*c;
lem(2)=0.25*T*c;
lem(3)=-0.75*T*c;
lem(4)=-0.75*c;
DX=[(1-cos(TW(1,1,1)))*cos(SW) (1-cos(TW(1,1,2)))*cos(SW)...
(1-cos(TW(1,1,2)))*cos(SW) (1-cos(TW(1,1,1)))*cos(SW)].*lem;
DY=-[sin(TW(1,1,1))*sin(dihed)*cos(SW) sin(TW(1,1,2))*sin(dihed)*cos(SW)...
sin(TW(1,1,2))*sin(dihed)*cos(SW) sin(TW(1,1,1))*sin(dihed)*cos(SW)].*lem;
DZ=[sin(TW(1,1,1))*cos(dihed) sin(TW(1,1,2))*cos(dihed) sin(TW(1,1,2))*cos(dihed)...
sin(TW(1,1,1))*cos(dihed)].*lem;
wingx=[0 0.25*c+b*tan(SW)-0.25*T*c 0.25*c+b*tan(SW)+0.75*T*c c]+ox+DX;
wingy=[0 b*cos(dihed) b*cos(dihed) 0]+oy+DY;
wingz=[0 b*sin(dihed) b*sin(dihed) 0]+oz+DZ;
%%%%%%%%%%%%%%%%%
%Plotting hinge %
%%%%%%%%%%%%%%%%%
if flapped==1
[flapx flapy flapz]=drawhinge(wingx,wingy,wingz,fc);
end
%figure(2) %UNCOMMENT THESE ROWS TO DRAW WING OUTLINES
% plot3(wingx,wingy,wingz);
% hold on
%if sym==1
%plot3(wingx,-wingy,wingz);
%end
%hold on
%axis equal
if flapped==0
[p]=tmesh2(wingx,wingy,wingz,nx,ny,meshtype);
PX(:,:)=p(:,:,1);
PY(:,:)=p(:,:,2);
PZ(:,:)=p(:,:,3);
else
tempx=wingx(3:4);
tempy=wingy(3:4);
tempz=wingz(3:4);
wingx(3:4)=fliplr(flapx(1:2));
wingy(3:4)=fliplr(flapy(1:2));
wingz(3:4)=fliplr(flapz(1:2));
flapx(3:4)=tempx;
flapy(3:4)=tempy;
flapz(3:4)=tempz;
[p]=tmesh2(wingx,wingy,wingz,nx,ny,meshtype);
[q]=tmesh2(flapx,flapy,flapz,fnx,ny,meshtype);
r=[];
for i=1:ny
count1=((1:nx)+(nx*(i-1)));
count2=(1:fnx)+(fnx*(i-1));
r=[r;p(count1,:,:);q(count2,:,:)];
end
PX(:,:)=r(:,:,1);
PY(:,:)=r(:,:,2);
PZ(:,:)=r(:,:,3);
end
nx=nx+fnx;
%%%%%%%%%%%%%%%%%%%
%Panel plot.
%Collocation point tensor generation & plot.
%Vortex tensor generation & plot.
%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Loop over all panels on quad. Determines panel corners, %
% vortex coo-rds, and collocation coo-rds %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
[X_1_S,lemma_1_S_tot]=slope2(foil(1,1,1)); %element inboard camber slope
[X_2_S,lemma_2_S_tot]=slope2(foil(1,1,2)); %element outboard camber slope
t=0;
for j=0:(ny-1);
for i=0:(nx-1);
t=t+1;
px=PX(t,:);
py=PY(t,:);
pz=PZ(t,:);
if i==(nx-fnx-1) %if the panel is the rearest chordwise on wing, forward of flap.
for s=0:(nx-fnx-1);
HP(t-s,1,:)=[px(4) py(4) pz(4)];
HP(t-s,2,:)=[px(3) py(3) pz(3)];
% TEP=Trailing edge points, Vortex points on the trailing edge
if sym==1
%Port side points
HP(t-s+neqns,1,:)=[px(3) -py(3) pz(3)];
HP(t-s+neqns,2,:)=[px(4) -py(4) pz(4)];
end
end
end
if i==(nx-1); %if the panel is the rearest chordwise on both wing and flap
for s=0:(nx-1);
TEP1(t-s,1,:)=[px(4) py(4) pz(4)];
TEP1(t-s,2,:)=[px(3) py(3) pz(3)];
% TEP=Trailing edge points, Vortex points on the trailing edge
if sym==1
%Port side points
TEP1(t-s+neqns,1,:)=[px(3) -py(3) pz(3)];
TEP1(t-s+neqns,2,:)=[px(4) -py(4) pz(4)];
end
for u=0:(fnx-1) %Hinge points for flap (equals trailing points)
HP(t-u,1,:)=[px(4) py(4) pz(4)];
HP(t-u,2,:)=[px(3) py(3) pz(3)];
if sym==1
%Port side points
HP(t-u+neqns,1,:)=[px(3) -py(3) pz(3)];
HP(t-u+neqns,2,:)=[px(4) -py(4) pz(4)];
end
end
end
end
%%%%%%%%%%%%%%%%%%%%%%%
% Collocation point %
% tensor generation %
%%%%%%%%%%%%%%%%%%%%%%%
mx=sum(px(1:4))/4; %panel midpoint x-coord
my=sum(py(1:4))/4;
mz=sum(pz(1:4))/4;
bkx=(px(3)+px(4))/2; %panel rear edge avarage x-coord
C1(t,1)=(mx+bkx)/2; %SB-Collocation point x-coord.
C1(t,2)=(py(3)+py(4)+2*my)/4; %SB-Collocation point y-coord.
C1(t,3)=(pz(3)+pz(4)+2*mz)/4; %SB-Collocation point z-coord.
if sym==1
C2(t,1)=C1(t,1); %P-Collpoint x-coord.
C2(t,2)=-C1(t,2); %P-Collpoint y-coord.
C2(t,3)=C1(t,3); %P-Collpoint z-coord.
else
C2=[];
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%Vortex tensor generation and plot %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
ax=((px(1)+px(4))/2+px(1))*0.5; %vortex first point
ay=(3*py(1)+py(4))/4;
az=(3*pz(1)+pz(4))/4;
bx=((px(2)+px(3))/2+px(2))*0.5; %vortex second point
by=(3*py(2)+py(3))/4;
bz=(3*pz(2)+pz(3))/4;
V1(t,1,1)=ax;
V1(t,1,2)=ay;
V1(t,1,3)=az;
V1(t,2,1)=bx;
V1(t,2,2)=by;
V1(t,2,3)=bz;
if sym==1;
V1(t+neqns,1,1)=bx;
V1(t+neqns,1,2)=-by;
V1(t+neqns,1,3)=bz;
V1(t+neqns,2,1)=ax;
V1(t+neqns,2,2)=-ay;
V1(t+neqns,2,3)=az;
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Passus to compute camber slope at %
% Station %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
a3=(sum(dr(1:i+1))-0.25*dr(1+i))/c; %determining percent of chord
%Thanks, Domenico & Giancarlo
%Tortora at University of Naples
%for spotting an earlier error
%here.
lemma_1_S(t)=interp1(X_1_S,lemma_1_S_tot,a3,'pchip','extrap'); %element inboard camber slope %ADRIEN
lemma_2_S(t)=interp1(X_2_S,lemma_2_S_tot,a3,'pchip','extrap'); %element outboard camber slope %ADRIEN
S(t)=(lemma_1_S(t)*(ny-j)+lemma_2_S(t)*(j))/ny; %avarage slope for panels on
if sym==1
S(t+neqns)=S(t);
end
end
end
C=[C1;C2];
V=V1;
Vor=[TEP1(:,1,:) HP(:,1,:) V(:,:,:) HP(:,2,:) TEP1(:,2,:)];
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% calculating normals %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
N=normals4(C,V,S);
V=Vor;
if sym==1
PX2(:,1)=PX(:,2);
PX2(:,2)=PX(:,1);
PX2(:,3)=PX(:,4);
PX2(:,4)=PX(:,3);
PX2(:,5)=PX2(:,1);
PY2(:,1)=PY(:,2);
PY2(:,2)=PY(:,1);
PY2(:,3)=PY(:,4);
PY2(:,4)=PY(:,3);
PY2(:,5)=PY2(:,1);
PZ2(:,1)=PZ(:,2);
PZ2(:,2)=PZ(:,1);
PZ2(:,3)=PZ(:,4);
PZ2(:,4)=PZ(:,3);
PZ2(:,5)=PZ2(:,1);
PX=[PX;PX2];
PY=[PY;-PY2];
PZ=[PZ;PZ2];
end
P(:,:,1)=PX;
P(:,:,2)=PY;
P(:,:,3)=PZ;
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function [normal]=normals4(colloc,vortex,C_Slope)
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% NORMALS: Essential function for TORNADO
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% This function calculates the normals to
% each panel. Two vectors in the plane, the ones between
% the vortex points and the collocation point, defines
% the panel plane. Together with the vortex orientation
% the orientation of the normal is defined.
% Output normals are normalized.
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Author: Tomas Melin, KTH, Department of Aeronautics
% copyright 2000
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% CONTEXT: Essential function for TORNADO
% Called by: setup
% Calls: trot
% MATLAB 5.2 std fcns
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
N=[];
step=size(colloc);
[d e f]=size(vortex);
a=e/2;
b=a+1;
for t=1:step %Looping through panels
alpha=C_Slope(t);
for s=1:3 %Looping Through Dimensions.
ra(s)=vortex(t,a,s);
rb(s)=vortex(t,b,s);
rc(s)=colloc(t,s);
end
r0=rb-ra;
r0(1)=0; %fix to get normals to not point the right way
r1=rc-ra;
r2=rc-rb;
n=cross(r1,r2); %Passus to determine normal
nl=sqrt(sum((n.^2),2)); %of panel at collocationpoint.
R=n/nl; %Normalizing normal.
R2=trot3(r0,R,-alpha); %rotating wha trot
N=[N;R2'];
end
normal=N;
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function[x,y,z]=drawhinge(wx,wy,wz,fc);
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% DRAWHINGE: subsidary function to TORNADO %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Function that draws the hinge line on %
% on a wing division. It also returns the %
% coordinates on the foremost flap corners %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Called by: Geometry
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% INPUT: WX,WY,WZ = wing cornerpoint coor-
% dinates.
% fc is the percentage of total chord
% built up by the flap
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% OUTPUT: graph (in figure (2))
% flap cornerpoint coor-
% dinates
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
if isempty(fc);
x=[];
y=[];
z=[];
else
for i=0:1
a=[wx(1+i) wy(1+i) wz(1+i)];
b=[wx(4-i) wy(4-i) wz(4-i)];
c=b-a;
l=norm(c);
c_hat=c./l;
d=(1-fc)*l*c_hat;
r=a+d;
R1(i+1,:)=[r];
R2(i+1,:)=[r];
end
%plot(R1(:,1),R1(:,2));
%Uncomment rows below to draw flap
%figure(2)
%plot3(R2(:,1),R2(:,2),R2(:,3));
%hold on
x=[R1(:,1)'];
y=[R1(:,2)'];
z=[R1(:,3)'];
end
end
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function[p2]=trot3(hinge,p,alpha)
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% TROT: Auxillary rotation function
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% rotates point p around hinge alpha rads.%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% ref: Råde, Westergren, BETA 4th ed,
% studentlitteratur, 1998
% pp:107-108
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Author: Tomas Melin, KTH,Department of%