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plotWing.m
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plotWing.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 Version 1.2 %%
% March 27, 2008 %%
% File: plotWing.m %%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Inputs:
% XW - x-coordinate of theoretical wing apex
% ZW - z-coordinate of theoretical wing apex
% ALIW - angle of incidence of the wing
% CHRDR - root chord (at centerline)
% CHRDBP - chord at breakpoint if outer and inner planforms exist
% CHRDTP - chord at tip
% SSPN - the semi-span of the wing (i.e. b/2)
% SSPNOP - the span of the outer planform measured from CHRDBP to CHRDTP
% SAVSI - the sweep of the inner planform
% SAVSO - the sweep of the outer planform
% CHSTAT - fraction of chord where sweep is measured from (i.e. 0.25)
% DHDADI - dihedral of the inner planform
% DHDADO - dihedral of the outer planform
% SPANFI - inner span position of flap
% SPANFO - outer span position of flap
% CHRDFI - chord position (wrt to LE) of flap at SPANFI
% CHRDFO - chord position (wrt to LE) of flap at SPANFO
% TC - t/c of the airfoil (i.e. 0.09, 0.12, 0.18, etc.)
% wgres - resolution of the planform(s) (meshgrid)
function 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,SPANFI_A,SPANFO_A,CHRDFI_A,CHRDFO_A,DELTAR,DELTAL,TC_WG,wgres)
% Determine if there is an outer planform
if SSPNOP_WG == 0
% Compute aspect ratio and taper ratio of wing
AR_wg=2*(SSPN_WG*2)/(CHRDR_WG+CHRDTP_WG);
TR_wg=CHRDTP_WG/CHRDR_WG;
% Allocate memory for arrays
X_wg=[];
Y_wg=[];
Z_wg=[];
di_wg=[]; % Dihedral spanwise
iw=[]; % Wing incidence chordwise
% Determine the leading edge sweep using CHSTAT
sweep = atand(tand(SAVSI_WG)-(4*(0-CHSTAT_WG)*(1-TR_wg))/(AR_wg*(1+TR_wg)));
% Determine the X and Y coordinates of the wing using taper ratio
% and sweep
for i=1:1:(wgres+1)
sw=(i-1)*SSPN_WG/wgres*tand(sweep);
for j=1:1:(wgres+1)
X_wg(i,j) = (((j-1)*CHRDR_WG/wgres)*(1-(i-1)*TR_wg/(wgres*TR_wg/(1-TR_wg))))+sw;
Y_wg(j,i) = (j-1)*SSPN_WG/wgres;
end
end
% Determine the shape of the airfoil given a TC ratio
% Determine the dihedral spanwise and wing incidence chordwise
% Determine flap deflection
for i=1:1:(wgres+1)
for j=1:1:(wgres+1)
c=X_wg(j,wgres+1)-X_wg(j,1);
xval=X_wg(j,i)-X_wg(j,1);
Z_wg(j,i)=TC_WG*5*c*(0.2969.*(xval/c).^0.5-0.126.*(xval/c)-...
0.3516.*(xval/c).^2+0.2843.*(xval/c).^3-0.1015.*(xval/c).^4);
di_wg(j,i)=(j-1)*SSPN_WG/wgres*tand(DHDADI_WG);
iw(j,i)=(i-1)*c/wgres*tand(-1*ALIW);
%df(j,i)=(i-1)*CHRDR_WG/wgres*tand(-1*DELTA);
df(j,i)=(i-1)*c/wgres*tand(-1*DELTA);
daL(j,i)=(i-1)*c/wgres*tand(-1*DELTAL);
daR(j,i)=(i-1)*c/wgres*tand(-1*DELTAR);
l(j)=j;
end
end
% FLAP CALCULATIONS **************************************************
%Y_wg2 = Y_wg;
% Allocate memory for arrays
I = []; % Intermediate array
Iy = []; % Overflow array
Ii = []; % Indices of inner span
Io = []; % Indices of outer span
l1 = []; % Indices of Flap chord length
l2 = []; % Indices of Chord length - flap chord length
ind = []; % Indices where flap exists
% Correct flap span for MATLAB plotting
if SPANFO_F > (SSPN_WG-SSPN_WG/(wgres+1))
SPANFO_F = SPANFO_F + SSPN_WG/(wgres+1);
end
% Correct for outboard control surfaces
if ((SPANFI_F-SSPN_WG/(wgres+1)) < SPANFO_A) && (SPANFO_F > SPANFO_A)
SPANFI_F = SPANFI_F - SSPN_WG/(wgres+1);
end
% Obtain indices of wing where flap exists (along span)
[I,Iy] = find((Y_wg >= SPANFI_F) & (Y_wg <= SPANFO_F));
Iymin = min(I); % Inboard index value of flap (inside)
Iymax = max(I); % Outboard index value of flap (inside)
Iyminf = Iymin+1; % Inboard index value of flap (outside)
Iymaxf = Iymax-1; % Outboard index value of flap (outside)
% Clean up array I
for i=Iyminf:Iymaxf, ind((i)-(Iyminf-1))=i;, end
%Obtain Ii and Io
for i=1:Iymin-1, Ii(i)=i;, end
for i=Iymax+1:(wgres+1), Io((i-1)-(Iymax-1))=i;, end
% Chordlength at flap inboard location (used for outboard location)
ci=X_wg(Iymin,wgres+1)-X_wg(Iymin,1);
% Number of indices that the flaps spans across (chordwise)
fc=int32(CHRDFI_F/ci*wgres);
% Obtain L2 and l1
for i=1:fc, l2(i)=(wgres+1)-(i-1);, end
for i=1:(wgres)-fc, l1(i)=i;, end
Y_flap = Y_wg; % Initialize flap to the wing matrix
% The following statements core out the flap matrix to leave
% only the flap area
Y_flap(Ii,l2) = NaN;
Y_flap(Io,l2) = NaN;
Y_flap(l,l1) = NaN;
Y_wg(ind,l2) = NaN; % Core out the flap area in the wing
% Adjust the flap deflection matrix to line up LE of flap with wing
%df = df - df(1,(wgres+1)-fc);
for i=1:(wgres+1)
dft = df(i,(wgres+1)-fc);
for j=1:(wgres+1)
df(i,j) = df(i,j) - dft;
end
end
% AILERON CALCULATIONS ************************************************
clear I Iy Ii Io l1 l2 ind Iymin Iymax Iyminf Iymaxf ci fc
I = []; % Intermediate array
Iy = []; % Overflow array
Ii = []; % Indices of inner span
Io = []; % Indices of outer span
l1 = []; % Indices of aileron chord length
l2 = []; % Indices of Chord length - aileron chord length
ind = []; % Indices where aileron exists
% Correct aileron span for MATLAB plotting
if SPANFO_A > (SSPN_WG-SSPN_WG/(wgres+1))
SPANFO_A = SPANFO_A + SSPN_WG/(wgres+1);
end
% Correct for outboard control surfaces
if ((SPANFI_A-SSPN_WG/(wgres+1)) < SPANFO_F) && (SPANFO_A > SPANFO_F)
SPANFI_A = SPANFI_A - SSPN_WG/(wgres+1);
%SPANFI_A = SPANFO_F - SSPN_WG/(wgres+1);
end
% Obtain indices of wing where aileron exists (along span)
[I,Iy] = find((Y_wg >= SPANFI_A) & (Y_wg <= SPANFO_A));
Iymin = min(I); % Inboard index value of aileron (inside)
Iymax = max(I); % Outboard index value of aileron (inside)
Iyminf = Iymin+1; % Inboard index value of aileron (outside)
Iymaxf = Iymax-1; % Outboard index value of aileron (outside)
% Clean up array I
for i=Iyminf:Iymaxf, ind((i)-(Iyminf-1))=i;, end
%Obtain Ii and Io
for i=1:Iymin-1, Ii(i)=i;, end
for i=Iymax+1:(wgres+1), Io((i-1)-(Iymax-1))=i;, end
% Chordlength at aileron inboard location (used for outboard location)
ci=X_wg(Iymin,wgres+1)-X_wg(Iymin,1);
% Number of indices that the aileron spans across (chordwise)
fc=int32(CHRDFI_A/ci*wgres);
% Obtain L2 and l1
for i=1:fc, l2(i)=(wgres+1)-(i-1);, end
for i=1:(wgres)-fc, l1(i)=i;, end
Y_aileron = Y_wg; % Initialize flap to the wing matrix
% The following statements core out the aileron matrix to leave
% only the aileron area
Y_aileron(Ii,l2) = NaN;
Y_aileron(Io,l2) = NaN;
Y_aileron(l,l1) = NaN;
Y_wg(ind,l2) = NaN; % Core out the aileron area in the wing
% Adjust the flap deflection matrix to line up LE of flap with wing
%df = df - df(1,(wgres+1)-fc);
for i=1:(wgres+1)
daLT = daL(i,(wgres+1)-fc);
daRT = daR(i,(wgres+1)-fc);
for j=1:(wgres+1)
daL(i,j) = daL(i,j) - daLT;
daR(i,j) = daR(i,j) - daRT;
end
end
% Plot the surfaces of the wing
% Upper and lower right, upper and lower left
surf(X_wg+XW,Y_wg,Z_wg+ZW+iw+di_wg,'EdgeColor','k','DisplayName','Wing Upper-Stb.')
surf(X_wg+XW,Y_wg,-1*Z_wg+ZW+iw+di_wg,'EdgeColor','k','DisplayName','Wing Lower-Stb.')
surf(X_wg+XW,-1.*Y_wg,Z_wg+ZW+iw+di_wg,'EdgeColor','k','DisplayName','Wing Upper-Port')
surf(X_wg+XW,-1.*Y_wg,-1*Z_wg+ZW+iw+di_wg,'EdgeColor','k','DisplayName','Wing Lower-Port')
if CHRDFI_F > 0
% Plot the surfaces of the flap
% Upper and lower right, upper and lower left
surf(X_wg+XW,Y_flap,Z_wg+ZW+iw+di_wg+df,'EdgeColor','r','DisplayName','Flap Upper-Stb.')
surf(X_wg+XW,Y_flap,-1*Z_wg+ZW+iw+di_wg+df,'EdgeColor','r','DisplayName','Flap Lower-Stb.')
surf(X_wg+XW,-1.*Y_flap,Z_wg+iw+di_wg+ZW+df,'EdgeColor','r','DisplayName','Flap Upper-Port')
surf(X_wg+XW,-1.*Y_flap,-1*Z_wg+iw+di_wg+ZW+df,'EdgeColor','r','DisplayName','Flap Lower-Port')
end
if CHRDFI_A > 0
% Plot the surfaces of the flap
% Upper and lower right, upper and lower left
surf(X_wg+XW,Y_aileron,Z_wg+ZW+iw+di_wg+daR,'EdgeColor','b','DisplayName','Aileron Upper-Stb.')
surf(X_wg+XW,Y_aileron,-1*Z_wg+ZW+iw+di_wg+daR,'EdgeColor','b','DisplayName','Aileron Lower-Stb.')
surf(X_wg+XW,-1.*Y_aileron,Z_wg+iw+di_wg+ZW+daL,'EdgeColor','b','DisplayName','Aileron Upper-Port')
surf(X_wg+XW,-1.*Y_aileron,-1*Z_wg+iw+di_wg+ZW+daL,'EdgeColor','b','DisplayName','Aileron Lower-Port')
end
else
% Inboard and outboard panel geometry
wgreso=int32(SSPNOP_WG/SSPN_WG*wgres);
wgresi=wgres-wgreso;
% Inboard and outboard aspect ratios
ARi_wg=2*((SSPN_WG-SSPNOP_WG)*2)/(CHRDR_WG+CHRDBP_WG);
ARo_wg=2*(SSPNOP_WG*2)/(CHRDBP_WG+CHRDTP_WG);
% Inboard and outboard taper ratios
TRi_wg=CHRDBP_WG/CHRDR_WG;
TRo_wg=CHRDTP_WG/CHRDBP_WG;
% Allocate memory for arrays
Xi_wg=[];
Xo_wg=[];
Yi_wg=[];
Yo_wg=[];
Zi_wg=[];
Zo_wg=[];
dii_wg=[];
dio_wg=[];
iwi=[];
iwo=[];
%Inboard and outboard leading edge sweep
sweepi = atand(tand(SAVSI_WG)-(4*(0-CHSTAT_WG)*(1-TRi_wg))/(ARi_wg*(1+TRi_wg)));
sweepo = atand(tand(SAVSO_WG)-(4*(0-CHSTAT_WG)*(1-TRo_wg))/(ARo_wg*(1+TRo_wg)));
% Determine the X and Y coordinates of the inboard planform using
% taper ratio and sweep
for i=1:1:(wgres+1)
sw=(i-1)*(SSPN_WG-SSPNOP_WG)/wgres*tand(sweepi);
for j=1:1:(wgres+1)
Xi_wg(i,j) = (((j-1)*CHRDR_WG/wgres)*(1-(i-1)*TRi_wg/(wgres*TRi_wg/(1-TRi_wg))))+sw;
Yi_wg(j,i) = (j-1)*(SSPN_WG-SSPNOP_WG)/wgres;
end
end
% Determine the shape of the airfoil given a TC ratio
% Determine the dihedral spanwise and wing incidence chordwise
% For inboard planform
for i=1:1:(wgres+1)
for j=1:1:(wgres+1)
c=Xi_wg(j,wgres+1)-Xi_wg(j,1);
xval=Xi_wg(j,i)-Xi_wg(j,1);
Zi_wg(j,i)=TC_WG*5*c*(0.2969.*(xval/c).^0.5-0.126.*(xval/c)-...
0.3516.*(xval/c).^2+0.2843.*(xval/c).^3-0.1015.*(xval/c).^4);
dii_wg(j,i)=(j-1)*(SSPN_WG-SSPNOP_WG)/wgres*tand(DHDADI_WG);
iwi(j,i)=(i-1)*c/wgres*tand(-1*ALIW);
end
end
% Determine the X and Y coordinates of the outboard planform using
% taper ratio and sweep
for i=1:1:(wgres+1)
sw=(i-1)*(SSPNOP_WG)/wgres*tand(sweepo);
for j=1:1:(wgres+1)
Xo_wg(i,j) = (((j-1)*CHRDBP_WG/wgres)*(1-(i-1)*TRo_wg/(wgres*TRo_wg/(1-TRo_wg))))+sw+Xi_wg(wgres+1,1);
Yo_wg(j,i) = (j-1)*(SSPNOP_WG)/wgres + (SSPN_WG-SSPNOP_WG);
end
end
% Determine the shape of the airfoil given a TC ratio
% Determine the dihedral spanwise and wing incidence chordwise
% For outboard planform
for i=1:1:(wgres+1)
for j=1:1:(wgres+1)
c=Xo_wg(j,wgres+1)-Xo_wg(j,1);
xval=Xo_wg(j,i)-Xo_wg(j,1);
Zo_wg(j,i)=TC_WG*5*c*(0.2969.*(xval/c).^0.5-0.126.*(xval/c)-...
0.3516.*(xval/c).^2+0.2843.*(xval/c).^3-0.1015.*(xval/c).^4);
dio_wg(j,i)=(j-1)*(SSPNOP_WG)/wgres*tand(DHDADO_WG);
iwo(j,i)=(i-1)*c/wgres*tand(-1*ALIW);
end
end
% Plot the surfaces of the inboard planform
% Upper and lower right, upper and lower left
surf(Xi_wg+XW,Yi_wg,Zi_wg+ZW+iwi+dii_wg,'EdgeColor','k','DisplayName','Wing In. Upper-Stb.')
surf(Xi_wg+XW,Yi_wg,-1.*Zi_wg+ZW+iwi+dii_wg,'EdgeColor','k','DisplayName','Wing In. Lower-Stb.')
surf(Xi_wg+XW,-1.*Yi_wg,Zi_wg+ZW+iwi+dii_wg,'EdgeColor','k','DisplayName','Wing In. Upper-Port')
surf(Xi_wg+XW,-1.*Yi_wg,-1.*Zi_wg+ZW+iwi+dii_wg,'EdgeColor','k','DisplayName','Wing In. Lower-Port')
% Plot the surfaces of the outboard planform
% Upper and lower right, upper and lower left
surf(Xo_wg+XW,Yo_wg,Zo_wg+ZW+iwo+(SSPN_WG-SSPNOP_WG)*tand(DHDADI_WG)+dio_wg,'EdgeColor','k','DisplayName','Wing Out. Upper-Stb.')
surf(Xo_wg+XW,Yo_wg,-1.*Zo_wg+ZW+iwo+(SSPN_WG-SSPNOP_WG)*tand(DHDADI_WG)+dio_wg,'EdgeColor','k','DisplayName','Wing Out. Lower-Stb.')
surf(Xo_wg+XW,-1.*Yo_wg,Zo_wg+ZW+iwo+(SSPN_WG-SSPNOP_WG)*tand(DHDADI_WG)+dio_wg,'EdgeColor','k','DisplayName','Wing Out. Upper-Port')
surf(Xo_wg+XW,-1.*Yo_wg,-1.*Zo_wg+ZW+iwo+(SSPN_WG-SSPNOP_WG)*tand(DHDADI_WG)+dio_wg,'EdgeColor','k','DisplayName','Wing Out. Lower-Port')
end