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fViscCorr2.m
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fViscCorr2.m
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function [outdata]=fViscCorr(geo,state,lattice,results,ref);
clalpha=2*pi;
[rho,a,p,mu]=ISAtmosphere(state.ALT);
Re=rho*state.AS*ref.C_mac/mu;
p_dyn=(state.rho*state.AS^2)/2; %Dynamic Pressure,
[a b]=size(geo.ny); %number of partitions
for i=1:b
spp(:,i)=(geo.ny(:,i)).*(geo.symetric+1)' ; %strips per partition
end
[lc lb sf]=fLocal_chord3(geo,lattice); %Local chords on each strip.
%Local strip width.
%Span Fraction, how far out on panel the strip is.
ls=lc.*lb; %Strip area
F0=fStripforce(geo,results,lattice,state); %This is the lift force on each panel
m=0;
for i=1:a %% Per wing loop
for j=1:geo.nelem(i) %% Per partition loop
Pinner=profilegen(geo.foil(i,j,1));
Pouter=profilegen(geo.foil(i,j,2));
alpha=0;
for k=1:spp(i,j) %Strip
m=m+1;
Pmix_yu=Pinner(:,2)*(1-sf(m))+Pouter(:,2)*(sf(m));
Pmix_yl=Pinner(:,3)*(1-sf(m))+Pouter(:,3)*(sf(m));
[a void]=size(Pmix_yu);
[b void]=size(Pmix_yl);
Pmix_yl(end)=Pmix_yu(end); %closing TE gap
Z=[[a b];[(0:0.01:1)' Pmix_yu];[(0:0.01:1)' Pmix_yl]]; %Airfoil file format
delta_alpha=10;
%Converge towards prescribed cl
while abs(delta_alpha)>0.0001;
[strip]=fPablo(Z,alpha*180/pi,Re);
cl=strip.cl;
cl_inv=F0(m)/(p_dyn*ls(m));
delta_cl=cl-cl_inv;
delta_alpha=-delta_cl/clalpha;
alpha=alpha+delta_alpha;
cd=strip.cd;
end
outdata.Striplift(m)=cl*(p_dyn*ls(m));
outdata.Stripdrag(m)=cd*(p_dyn*ls(m));
outdata.Stripalpha(m)=alpha;
outdata.upperbl(m,:)=strip.upperbl;
outdata.lowerbl(m,:)=strip.lowerbl;
end
%Not finished yet
%outdata.partitionlift(i,j)=sum(outdata.Striplift((end-XXX))
%outdata.partitiondrag(i,j)=
end
end
outdata.totalliftcoeff= sum(outdata.Striplift)./(ref.S_ref*p_dyn);
outdata.totalvdragcoeff= sum(outdata.Stripdrag)./(ref.S_ref*p_dyn);
end %Function
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function[lc lb sf]=fLocal_chord3(geo,lattice)
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Geometry function
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Computes the Local chord at each collocation
% point row.
%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Author: Tomas Melin, KTH, Department of
% Aeronautics, copyright 2002
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Context: Auxillary function for TORNADO
% Called by: TORNADO spanload
% Calls: None
% Loads: None
% Generates: Local chord vector lc, same
% order as colloc, N, and the others
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
[a b]=size(geo.ny); %number of partitions
for i=1:b
spp(:,i)=(geo.ny(:,i)).*(geo.symetric+1)' ;%strips per partition
end
[indx1 indx2]=size(geo.b);
for s=1:indx1; %Looping over wings
CHORDS(s,1)=geo.c(s); %calculating chords of first element
end
for s=1:indx1 %Looping over wings
for t=1:indx2 %Looping over partitions
%Chord loop, generating chords for wing partitions
CHORDS(s,t+1)=CHORDS(s,t)*geo.T(s,t); %calculating
%element root-chord
end
end
lc=[]; %Local chord vector.
lb=[]; %Local span vector.
panelchords1=sqrt(sum((lattice.XYZ(:,1,:)-lattice.XYZ(:,4,:)).^2,3)); %inboard
panelchords2=sqrt(sum((lattice.XYZ(:,2,:)-lattice.XYZ(:,3,:)).^2,3)); %outboard
panelchords3=(panelchords1+panelchords2)/2; %Chord of each panel, CAUTION
%this is really camber line
%length, so not really chord
%for very cambered profiles
%Local chord loop
for i=1:indx1; %Wing
for j=1:indx2; %Partition
lemma=[]; %local chord lemma vector.
chordwisepanels=geo.nx(i,j)+geo.fnx(i,j); %number of panels chordwise on
%this partition
for k=1:geo.ny(i,j) %loop over panel strips.
if geo.ny(i,j)~=0
lemma=[lemma sum(panelchords3(1:chordwisepanels))];
panelchords3=panelchords3((chordwisepanels+1):end);
%size(panelchords3);
end
end
if geo.symetric(i)==1 %symmetric wings got two sides
lc=[lc lemma lemma];
panelchords3=panelchords3((chordwisepanels*geo.ny(i,j)+1):end);
else
lc=[lc lemma];
end
end
end
%Local span loop
A1=((lattice.XYZ(:,1,:)-lattice.XYZ(:,2,:)));
panelspan=sqrt(A1(:,:,2).^2+A1(:,:,3).^2); %span of each panel
knx=geo.nx+geo.fnx; %total number of chordwise panels
m=0;
for i=1:indx1; %Wing
for j=1:indx2; %Partition
for k=1:spp(i,j) %Strip
m=m+1;
lb(m)=panelspan(1);
panelspan=panelspan((knx(i,j)+1):end);
end
end
end
panelmid=sqrt(sum((lattice.COLLOC(:,2:3).^2),2));
panelmin=sqrt(sum((lattice.XYZ(:,1,:).^2),3));
panelmax=sqrt(sum((lattice.XYZ(:,2,:).^2),3));
sf=[];
for i=1:indx1; %Wing
for j=1:indx2; %Partition
m=0;
for k=1:spp(i,j) %Strip
m=m+1;
stripmid(m)=panelmid(1);
stripmax(m)=max([panelmin(1) panelmax(1)]);
panelmid=panelmid((knx(i,j)+1):end);
panelmin=panelmin((knx(i,j)+1):end);
panelmax=panelmax((knx(i,j)+1):end);
end
sf=[sf stripmid/max(stripmax)];
stripmid=[];
stripmax=[];
m=0;
end
end
end%function
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function [profile]=profilegen(foil)
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% SLOPE: Essential function for TORNADO %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Calculates the angle of normalrotation due to camber %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Author:Adrien Bérard, KTH, Department of Aeronautics %
% and
% Tomas Melin, University of Bristol, Aero Dept.
%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% CONTEXT: subsidiary function for TORNADO %
% Called by: geometry %
% Calls: MATLAB 5.2 std fcns %
% %
%
% Load: the airfoil data points
%% Check type, file or formula... %TM20070206
%% Updated function to give wing profile as outdata:
if isempty(str2num((cell2mat(foil))))==0
TYPE=1; %Naca xxxx profile, see case 1
elseif isempty(str2num((cell2mat(foil))))
TYPE=2; %Airfoil from file, see case 2
else
disp('Foil error, flatplate assumed')
xa=[0 0 0];
angle=[0 0 0];
return
end
%% First type
switch TYPE
case 1
%The Airfoil camber can be described as a function, NACA 4 digits
foil=str2num(cell2mat(foil));
m=fix(foil/1000); %gives first NACA-4 number
lemma=foil-m*1000;
p=fix(lemma/100); %gives second NACA-4 number
t=(foil-m*1000-p*100)/100;
p=p/10;
m=m/100;
xa=0:0.01:1;
for i=1:101
if xa(i)<p
a(i)=(m/(p^2)*xa(i)*(2*p-xa(i)));
else
a(i)= m/((1-p)^2)* ((1-2*p)+2*p*xa(i)-xa(i)^2);
end
end
angle=atan(diff(a)./diff(xa));
angle=[angle angle(end)];
yt=t*5*(0.2969.*xa.^0.5 -0.1260.*xa -0.3516.*xa.^2 +0.2843.*xa.^3 -0.1015.*xa.^4);
xu=xa-yt.*sin(angle);
yu=a+yt.*cos(angle);
xl=xa+yt.*sin(angle);
yl=a-yt.*cos(angle);
yui=interp1(xu,yu,xa);
yli=interp1(xl,yl,xa);
profile=[[xa' yui' yli']];
return
%% Second Type
case 2
% Load the airfoil data points
settings=config('startup');
cd(settings.afdir)
A=load(char(foil));
cd(settings.hdir)
% Take the number of data points in the data file
Nu=A(1,1); % for the upper surface
Nl=A(1,2); % for the lower surface
%Upper surface
Xu = A(2:Nu+1,1)/A(Nu+1,1); %% It is divided by A(L+1,1), which is the max absciss of the aifoil, in order to normalize the airfoil to a chord c=1
Yu = A(2:Nu+1,2)/A(Nu+1,1);
% Lower surface
Xl = A(Nu+2:end,1)/A(Nu+1,1);
Yl = A(Nu+2:end,2)/A(Nu+1,1);
xa=0:0.01:1;
yui=interp1(Xu,Yu,xa,'spline');
yli=interp1(Xl,Yl,xa,'spline');
profile=[[xa' yui' yli']];
return
end
end %function
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function [F0]=fStripforce(geo,results,lattice,state)
%This lemma function computes the aerodynamic force on each strip.
IL=spanload7(results,geo,lattice,state); %This is the Inviscous_Lift on each panel.
[ai bi]=size(geo.nx); %number of wings and panels
cnx=geo.nx+geo.fnx; %corrected number of xpanels
for i=1:geo.nwing;
cny(i,:)=geo.ny(i,:).*(geo.symetric(i)+1); %corrected number of ypanels
end
m=0;
for i=1:ai %loop per wing
for j=1:bi %loop per partition
%Per partition, do:
%Add up all forces on each strip
index1=1;
index2=cnx(i,j);
for k=1:cny(i,j)
%per strip loop
m=m+1;
F0(m)=sum(IL(index1:index2));
index1=index1+cnx(i,j);
index2=index2+cnx(i,j);
end
end
end
end %function stripforce
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function [forceLift]=spanload7(results,geo,lattice,state)
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% CONFIG: Basic computation function %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Computes the spanload (force/meter) for
% all wings
%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Author: Tomas Melin, KTH, Department of%
% Aeronautics, copyright 2002 %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Context: Auxillary function for TORNADO%
% Called by: TORNADO SOlverloop %
% Calls: None %
% Loads: None %
% Generates: force per meter array
% (ystations X wings)
% Ystation array
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Revision history post alfa 1.0 %
% 2007-02-14 rho moved to state
% 2002-05-02
% input var T (taper) added to get local
% chords.
% input var AS (airspeed) added
% local chord computation function call added
%
%rho=config('rho'); %set density
lemma=size(geo.b); %number of partitions and wings
B2WTransform=[cos(state.betha)*cos(state.alpha), -sin(state.betha), cos(state.betha)*sin(state.alpha) ;...
cos(state.alpha)*sin(state.betha), cos(state.betha), sin(state.betha)*sin(state.alpha) ;...
-sin(state.alpha), 0, cos(state.alpha)];
noofpanels=sum(((geo.nx+geo.fnx).*geo.ny),2).*(geo.symetric'+1); %number of panels in total (symmetry disregarded)
lemma=size(results.F);
corrx=[];
corry=[];
corrz=[];
lemma2=size(geo.b);
for i=1:lemma2(1)
corry=[corry;ones(noofpanels(i),1)*geo.starty(i)];
corrz=[corrz;ones(noofpanels(i),1)*geo.startz(i)];
end
for i=1:lemma(1)
forceMagn(i)=-results.F(i,:)*lattice.N(i,:)'; %Force magnitude (3Dvector -> scalar)
%Aligned witn panel normals
lemma4(i,:)=B2WTransform*results.F(i,:)';
forceLift(i)=lemma4(i,3); %Lift on each panel, this is outdata for the
%viscous correction.
end
end%function
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%