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texport.m
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function [op]=texport(JID,fname,quest) %***
settings=config('startup');
cd(settings.odir)
switch(quest) %***
case(14) %***
load(strcat(JID,'-Cx'))
fid=fopen(strcat(fname,'.txt'),'w');
fprintf(fid,'%%Tornado exported result data. \n');
fprintf(fid,strcat(strcat('%%Date: ', date), '\n'));
fprintf(fid,strcat(strcat('%%JID: ', JID), '\n'));
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Solution condition: \n');
fprintf(fid,'\n');
fprintf(fid,'%4f', results.dwcond);
fprintf(fid,('\t %% Solver numerical condition. \n'));
fprintf(fid,'\n');
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%State: \n');
fprintf(fid,'\n');
fprintf(fid,'%4f', state.AS);
fprintf(fid,('\t %% Airspeed \n'));
fprintf(fid,'%4f', state.alpha);
fprintf(fid,('\t %% Angle of attack, [rad] \n'));
fprintf(fid,'%4f', state.betha);
fprintf(fid,('\t %% Angle of sideslip, [rad] \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f', state.P);
fprintf(fid,('\t %% Roll rate, [rad/s] \n'));
fprintf(fid,'%6f', state.Q);
fprintf(fid,('\t %% Pitch rate, [rad/s] \n'));
fprintf(fid,'%6f', state.R);
fprintf(fid,('\t %% Yaw rate, [rad/s] \n'));
fprintf(fid,'\n') ;
fprintf(fid,'%6f', state.rho);
fprintf(fid,('\t %% Air density, [kg/m^3] \n'));
fprintf(fid,'%6f', state.ALT);
fprintf(fid,('\t %% Altitude, [m] \n'));
fprintf(fid,'%6f', state.pgcorr);
fprintf(fid,('\t %% Prandtl-Glauert correction enabled, [1/0] \n')); %***Pradtl changed to Prandtl (AT)
fprintf(fid,'\n') ;
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Reference units: \n');
fprintf(fid,'\n');
fprintf(fid,'%6f', ref.S_ref);
fprintf(fid,('\t %% Reference area, [m^2] \n'));
fprintf(fid,'%6f', ref.C_mac);
fprintf(fid,('\t %% Mean Aero Chord, [m] \n'));
fprintf(fid,'%6f', ref.b_ref);
fprintf(fid,('\t %% Reference span, [m] \n'));
fprintf(fid,'\n');
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Coefficients: \n');
fprintf(fid,'\n');
fprintf(fid,'%6f', results.CL);
fprintf(fid,('\t %% CL \n'));
fprintf(fid,'%6f', results.CD);
fprintf(fid,('\t %% CD \n'));
fprintf(fid,'%6f', results.CY);
fprintf(fid,('\t %% CY \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f', results.Cl);
fprintf(fid,('\t %% Cl \n'));
fprintf(fid,'%6f', results.Cm);
fprintf(fid,('\t %% Cm \n'));
fprintf(fid,'%6f', results.Cn);
fprintf(fid,('\t %% Cn \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f', results.CX);
fprintf(fid,('\t %% CX \n'));
fprintf(fid,'%6f', results.CY);
fprintf(fid,('\t %% CY \n'));
fprintf(fid,'%6f', results.CZ);
fprintf(fid,('\t %% CZ \n'));
fprintf(fid,'\n');
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Alpha derivatives: \n');
fprintf(fid,'\n');
fprintf(fid,'%6f', results.CL_a);
fprintf(fid,('\t %% CL_a \n'));
fprintf(fid,'%6f', results.CD_a);
fprintf(fid,('\t %% CD_a \n'));
fprintf(fid,'%6f', results.CY_a);
fprintf(fid,('\t %% CY_a \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f', results.Cl_a);
fprintf(fid,('\t %% Cl_a \n'));
fprintf(fid,'%6f', results.Cm_a);
fprintf(fid,('\t %% Cm_a \n'));
fprintf(fid,'%6f', results.Cn_a);
fprintf(fid,('\t %% Cn_a \n'));
fprintf(fid,'\n');
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Beta derivatives: \n');
fprintf(fid,'\n');
fprintf(fid,'%6f', results.CL_b);
fprintf(fid,('\t %% CL_b \n'));
fprintf(fid,'%6f', results.CD_b);
fprintf(fid,('\t %% CD_b \n'));
fprintf(fid,'%6f', results.CY_b);
fprintf(fid,('\t %% CY_b \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f', results.Cl_b);
fprintf(fid,('\t %% Cl_b \n'));
fprintf(fid,'%6f', results.Cm_b);
fprintf(fid,('\t %% Cm_b \n'));
fprintf(fid,'%6f', results.Cn_b);
fprintf(fid,('\t %% Cn_b \n'));
fprintf(fid,'\n');
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Roll rate derivatives: \n');
fprintf(fid,'\n');
fprintf(fid,'%6f', results.CL_P);
fprintf(fid,('\t %% CL_P \n'));
fprintf(fid,'%6f', results.CD_P);
fprintf(fid,('\t %% CD_P \n'));
fprintf(fid,'%6f', results.CY_P);
fprintf(fid,('\t %% CY_P \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f', results.Cl_P);
fprintf(fid,('\t %% Cl_P \n'));
fprintf(fid,'%6f', results.Cm_P);
fprintf(fid,('\t %% Cm_P \n'));
fprintf(fid,'%6f', results.Cn_P);
fprintf(fid,('\t %% Cn_P \n'));
fprintf(fid,'\n');
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Pitch rate derivatives: \n');
fprintf(fid,'\n');
fprintf(fid,'%6f', results.CL_P);
fprintf(fid,('\t %% CL_P \n'));
fprintf(fid,'%6f', results.CD_P);
fprintf(fid,('\t %% CD_P \n'));
fprintf(fid,'%6f', results.CY_P);
fprintf(fid,('\t %% CY_P \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f', results.Cl_P);
fprintf(fid,('\t %% Cl_P \n'));
fprintf(fid,'%6f', results.Cm_P);
fprintf(fid,('\t %% Cm_P \n'));
fprintf(fid,'%6f', results.Cn_P);
fprintf(fid,('\t %% Cn_P \n'));
fprintf(fid,'\n');
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Yaw rate derivatives: \n');
fprintf(fid,'\n');
fprintf(fid,'%6f', results.CL_R);
fprintf(fid,('\t %% CL_R \n'));
fprintf(fid,'%6f', results.CD_R);
fprintf(fid,('\t %% CD_R \n'));
fprintf(fid,'%6f', results.CY_R);
fprintf(fid,('\t %% CY_R \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f', results.Cl_R);
fprintf(fid,('\t %% Cl_R \n'));
fprintf(fid,'%6f', results.Cm_R);
fprintf(fid,('\t %% Cm_R \n'));
fprintf(fid,'%6f', results.Cn_R);
fprintf(fid,('\t %% Cn_R \n'));
fprintf(fid,'\n');
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Control surface deflection derivatives: \n');
fprintf(fid,'%%CS #1 #2 #3 ... \n');
fprintf(fid,'\n');
fprintf(fid,'%6f \t', results.CL_d);
fprintf(fid,('\t %% CL_d \n'));
fprintf(fid,'%6f \t', results.CD_d);
fprintf(fid,('\t %% CD_d \n'));
fprintf(fid,'%6f \t', results.CY_d);
fprintf(fid,('\t %% CY_d \n'));
fprintf(fid,'\n');
fprintf(fid,'%6f \t', results.Cl_d);
fprintf(fid,('\t %% Cl_d \n'));
fprintf(fid,'%6f \t', results.Cm_d);
fprintf(fid,('\t %% Cm_d \n'));
fprintf(fid,'%6f \t', results.Cn_d);
fprintf(fid,('\t %% Cn_d \n'));
fprintf(fid,'%%--------------------------------------------- \n');
fprintf(fid,'%%Spanload: \n');
fprintf(fid,'%%Station 1 2 3 4...n \n');
fprintf(fid,'\n');
fprintf(fid,'%6f \t', full(results.ystation));
fprintf(fid,('\t %% Span station \n'));
fprintf(fid,'%6f \t', full(results.ForcePerMeter));
fprintf(fid,('\t %% Force Per Meter [N/m] \n'));
fprintf(fid,'%6f \t', full(results.CL_local));
fprintf(fid,('\t %% Spanwise local CL [-/m] \n'));
fprintf(fid,'\n');
fprintf(fid,'End of file');
fclose(fid);
disp(' ')
disp(' File written to:')
disp(strcat(strcat(pwd,'\'),strcat(fname,'.txt')));
disp(' ')
op=0;
cd(settings.hdir)
case(15) %***
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %***
%function infofile() %***
load(strcat(JID,'-Cx_drginf')) %***
%Output all information from breakdown to text file %***
fid=fopen(strcat(fname,'-drginf.txt'),'w'); %***
% Manipulating drag results matrices for output %***
%Initialising display variables %***
MASTDRGdisp=zeros(numbmhs+1,numbcls+1);TCDTINCdisp=zeros(numbmhs+1,numbcls+1); %***
CLHTAILdisp=zeros(numbmhs+1,numbcls+1);TCDWINCdisp=zeros(numbmhs+1,numbcls+1); %***
TTTHRSTdisp=zeros(numbmhs+1,numbcls+1);TCDCINCdisp=zeros(numbmhs+1,numbcls+1); %***
CLWINGAdisp=zeros(numbmhs+1,numbcls+1);dclwdcldisp=zeros(numbmhs+1,numbcls+1); %***
TTLTRMDdisp=zeros(numbmhs+1,numbcls+1);CMALPHAdisp=zeros(numbmhs+1,numbcls+1); %***
CDALPHAdisp=zeros(numbmhs+1,numbcls+1);DEALPHAdisp=zeros(numbmhs+1,numbcls+1); %***
MASTDIZdisp=zeros(numbmhs+1,numbcls+1);
fprintf(fid,'Drag and Associated Results from Polar Breakdown\n\n'); %***
% Total Drag (MASTDRG) %***
fprintf(fid,'---- Total Drag of Aircraft (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
MASTDRGdisp=MASTDRG; %***
MASTDRGdisp(1,:)=MASTDRGdisp(1,:)/10; %***
MASTDRGdisp(:,1)=MASTDRGdisp(:,1)/10; %***
for n=1:1:(size(MASTDRGdisp,1)) %***
fprintf(fid,'%10.2f',MASTDRGdisp(n,:)); %***
fprintf(fid,'\n'); %***
end %***
% Auto-Vortex Induced Drag of Wing (vorinrd) %***
fprintf(fid,'\n\n---- Auto-Vortex Induced Drag of Main Wing (Counts) ----\n'); %***
fprintf(fid,' / Operating Lift Coefficient\n\n'); %***
fprintf(fid,'%10.2f',(MASTDRG(1,:)/10)); %***
fprintf(fid,'\n'); %***
fprintf(fid,'%10.2f',vorinrd'); %***
fprintf(fid,'\n'); %***
% Auto-Vortex Induced Drag Factor of Wing (VORINDF) %***
fprintf(fid,'\n\n---- Wing Auto-Induced Drag Factor and Corresponding CL ----\n\n'); %***
fprintf(fid,' Drag Factor CL \n');
fprintf(fid,'%12.4f',VORINDF); %***
fprintf(fid,'%12.4f',VOINFCL); %***
fprintf(fid,'\n'); %***
% Equivalent Oswald Factor (OSWALDF) %***
fprintf(fid,'\n\n---- Equivalent Oswald Factor ----\n\n'); %***
fprintf(fid,'%12.4f',OSWALDF); %***
fprintf(fid,'\n'); %***
% Zero-Lift Drag Coefficient (EZELDRG) %***
fprintf(fid,'\n\n---- Zero-Lift Drag (Counts) ----\n\n'); %***
fprintf(fid,'%12.2f',EZELDRG); %***
fprintf(fid,'\n'); %***
% Form Drag as a Function of Operating Lift Coefficient (PROFCOR) %***
fprintf(fid,'\n\n---- Form Drag as a Function of Operating Lift Coefficient (Counts) ----\n'); %***
fprintf(fid,' / Operating Lift Coefficient\n\n'); %***
fprintf(fid,'%11.2f',(MASTDRG(1,:)/10)); %***
fprintf(fid,'\n'); %***
fprintf(fid,'%11.3f',PROFCOR); %***
fprintf(fid,'\n'); %***
% Trim Drag due to H-Tail Vortex-Induced Drag (TCDTINC) %***
fprintf(fid,'\n\n---- Trim Drag due to H-Tail Vortex-Induced Drag (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TCDTINCdisp=TCDTINC; %***
TCDTINCdisp(1,:)=MASTDRGdisp(1,:); %***
TCDTINCdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TCDTINCdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',TCDTINCdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',TCDTINCdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Lift Coefficient of H-Tail (CLHTAIL) %***
fprintf(fid,'\n\n---- Lift Coefficient of H-Tail ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
CLHTAILdisp=CLHTAIL; %***
CLHTAILdisp(1,:)=MASTDRGdisp(1,:); %***
CLHTAILdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(CLHTAILdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',CLHTAILdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',CLHTAILdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Trim Drag due to Wing Incremental Vortex-Induced Drag (TCDWINC) %***
fprintf(fid,'\n\n---- Trim Drag due to Wing Incremental Vortex-Induced Drag (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TCDWINCdisp=MASTDRG; %***
TCDWINCdisp(1,:)=MASTDRGdisp(1,:); %***
TCDWINCdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TCDWINCdisp,1)) %***
fprintf(fid,'%10.2f',TCDWINCdisp(n,:)); %***
fprintf(fid,'\n'); %***
end %***
% Tail Thrust (Negative Drag) due to Wing Downwash (TTTHRST) %***
fprintf(fid,'\n\n---- Tail Thrust (Negative Drag) due to Wing Downwash (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TTTHRSTdisp=TTTHRST; %***
TTTHRSTdisp(1,:)=MASTDRGdisp(1,:); %***
TTTHRSTdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TTTHRSTdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',TTTHRSTdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',TTTHRSTdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Incremental Compressibility Drag due to Wing Lift Increment (TCDCINC) %***
fprintf(fid,'\n\n---- Incremental Compressibility Drag due to Wing Lift Increment (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TCDCINCdisp=TCDCINC; %***
TCDCINCdisp(1,:)=MASTDRGdisp(1,:); %***
TCDCINCdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TCDCINCdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',TCDCINCdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',TCDCINCdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Actual Lift Coefficient of Main Wing (CLWINGA) %***
fprintf(fid,'\n\n---- Actual Lift Coefficient of Main Wing ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
CLWINGAdisp=CLWINGA; %***
CLWINGAdisp(1,:)=MASTDRGdisp(1,:); %***
CLWINGAdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(CLWINGAdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',CLWINGAdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',CLWINGAdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Rate Change of Wing Lift w.r.t. Global Lift Coefficient (dclwdcl) %***
fprintf(fid,'\n\n---- Rate Change of Wing Lift w.r.t. Global Lift Coefficient ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
dclwdcldisp=dclwdcl; %***
dclwdcldisp(1,:)=MASTDRGdisp(1,:); %***
dclwdcldisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(dclwdcldisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',dclwdcldisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',dclwdcldisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Total Trim Drag (TTLTRMD) %***
fprintf(fid,'\n\n---- Total Trim Drag of Aircraft (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TTLTRMDdisp=TTLTRMD; %***
TTLTRMDdisp(1,:)=MASTDRGdisp(1,:); %***
TTLTRMDdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TTLTRMDdisp,1)) %***
fprintf(fid,'%10.2f',TTLTRMDdisp(n,:)); %***
fprintf(fid,'\n'); %***
end %***
% Pitching Moment Gradient due to AoA (CMALPHA) %***
fprintf(fid,'\n\n---- Pitching Moment Gradient due to Angle of Attack (***Units?) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
CMALPHAdisp=CMALPHA; %***
CMALPHAdisp(1,:)=MASTDRGdisp(1,:); %***
CMALPHAdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(CMALPHAdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',CMALPHAdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',CMALPHAdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Rate Change of Total Drag w.r.t. AoA (CDALPHA) %***
fprintf(fid,'\n\n---- Rate Change of Total Drag w.r.t. Angle of Attack (***Units?)----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
CDALPHAdisp=CDALPHA; %***
CDALPHAdisp(1,:)=MASTDRGdisp(1,:); %***
CDALPHAdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(CDALPHAdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',CDALPHAdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',CDALPHAdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Difference Between Given AoA and Zero-Lift AoA (DEALPHA) %***
fprintf(fid,'\n\n---- Difference Between Given AoA and Zero-Lift AoA (rad)----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
DEALPHAdisp=DEALPHA; %***
DEALPHAdisp(1,:)=MASTDRGdisp(1,:); %***
DEALPHAdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(DEALPHAdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',DEALPHAdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',DEALPHAdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Compressibility Drag Matrix Adjusted for Wing Incremental Lift Effect (MASTDIZ) %***
fprintf(fid,'\n\n---- Compressibility Drag Matrix Adjusted for Wing Incremental Lift Effect (Counts)----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
MASTDIZdisp=MASTDIZ; %***
MASTDIZdisp(1,:)=MASTDRGdisp(1,:); %***
MASTDIZdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(MASTDIZdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',MASTDIZdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',MASTDIZdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
fprintf(fid,'\n\n*** End of File ***'); %***
fclose(fid); %***
disp(' ') %***
disp(' File written to:') %***
disp(strcat(strcat(pwd,'\'),strcat(fname,'-drginf.txt'))); %***
op=0; %***
cd(settings.hdir) %***
%end %infofile function %***
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%function drgfile() %***
cd(settings.odir)
load(strcat(JID,'-Cx_drgout')) %***
%Output drag information from breakdown to text file %***
fid=fopen(strcat(fname,'-drgout.txt'),'w'); %***
% Manipulating drag results matrices for output %***
%otptcls=((MASTCLS(MASTCLS~=0))/10)'; %***
%otptmch=(MASTMCH/10)'; %***
%Initialising display variables %***
MASTDRGdisp=zeros(numbmhs+1,numbcls+1);TCDTINCdisp=zeros(numbmhs+1,numbcls+1); %***
TCDWINCdisp=zeros(numbmhs+1,numbcls+1);TTTHRSTdisp=zeros(numbmhs+1,numbcls+1); %***
TCDCINCdisp=zeros(numbmhs+1,numbcls+1);TTLTRMDdisp=zeros(numbmhs+1,numbcls+1); %***
CDALPHAdisp=zeros(numbmhs+1,numbcls+1);MASTDIZdisp=zeros(numbmhs+1,numbcls+1); %***
fprintf(fid,'Constituent Components of Drag from Polar Breakdown\n\n'); %***
% Total Drag (MASTDRG) %***
fprintf(fid,'---- Total Drag of Aircraft (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
MASTDRGdisp=MASTDRG; %***
MASTDRGdisp(1,:)=MASTDRGdisp(1,:)/10; %***
MASTDRGdisp(:,1)=MASTDRGdisp(:,1)/10; %***
for n=1:1:(size(MASTDRGdisp,1)) %***
fprintf(fid,'%10.2f',MASTDRGdisp(n,:)); %***
fprintf(fid,'\n'); %***
end %***
% Auto-Vortex Induced Drag of Wing (vorinrd) %***
fprintf(fid,'\n\n---- Auto-Vortex Induced Drag of Main Wing (Counts) ----\n'); %***
fprintf(fid,' / Operating Lift Coefficient\n\n'); %***
fprintf(fid,'%10.2f',(MASTDRG(1,:)/10)); %***
fprintf(fid,'\n'); %***
fprintf(fid,'%10.2f',vorinrd'); %***
fprintf(fid,'\n'); %***
% Auto-Vortex Induced Drag Factor of Wing (VORINDF) %***
fprintf(fid,'\n\n---- Wing Auto-Induced Drag Factor and Corresponding CL ----\n\n'); %***
fprintf(fid,' Drag Factor CL \n');
fprintf(fid,'%12.4f',VORINDF); %***
fprintf(fid,'%12.4f',VOINFCL); %***
fprintf(fid,'\n'); %***
% Zero-Lift Drag Coefficient (EZELDRG) %***
fprintf(fid,'\n\n---- Zero-Lift Drag (Counts) ----\n\n'); %***
fprintf(fid,'%12.2f',EZELDRG); %***
fprintf(fid,'\n'); %***
% Form Drag as a Function of Operating Lift Coefficient (PROFCOR) %***
fprintf(fid,'\n\n---- Form Drag as a Function of Operating Lift Coefficient (Counts) ----\n'); %***
fprintf(fid,' / Operating Lift Coefficient\n\n'); %***
fprintf(fid,'%11.2f',(MASTDRG(1,:)/10)); %***
fprintf(fid,'\n'); %***
fprintf(fid,'%11.3f',PROFCOR); %***
fprintf(fid,'\n'); %***
% Trim Drag due to H-Tail Vortex-Induced Drag (TCDTINC) %***
fprintf(fid,'\n\n---- Trim Drag due to H-Tail Vortex-Induced Drag (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TCDTINCdisp=TCDTINC; %***
TCDTINCdisp(1,:)=MASTDRGdisp(1,:); %***
TCDTINCdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TCDTINCdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',TCDTINCdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',TCDTINCdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Trim Drag due to Wing Incremental Vortex-Induced Drag (TCDWINC) %***
fprintf(fid,'\n\n---- Trim Drag due to Wing Incremental Vortex-Induced Drag (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TCDWINCdisp=MASTDRG; %***
TCDWINCdisp(1,:)=MASTDRGdisp(1,:); %***
TCDWINCdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TCDWINCdisp,1)) %***
fprintf(fid,'%10.2f',TCDWINCdisp(n,:)); %***
fprintf(fid,'\n'); %***
end %***
% Tail Thrust (Negative Drag) due to Wing Downwash (TTTHRST) %***
fprintf(fid,'\n\n---- Tail Thrust (Negative Drag) due to Wing Downwash (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TTTHRSTdisp=TTTHRST; %***
TTTHRSTdisp(1,:)=MASTDRGdisp(1,:); %***
TTTHRSTdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TTTHRSTdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',TTTHRSTdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',TTTHRSTdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Incremental Compressibility Drag due to Wing Lift Increment (TCDCINC) %***
fprintf(fid,'\n\n---- Incremental Compressibility Drag due to Wing Lift Increment (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TCDCINCdisp=TCDCINC; %***
TCDCINCdisp(1,:)=MASTDRGdisp(1,:); %***
TCDCINCdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TCDCINCdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',TCDCINCdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',TCDCINCdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Total Trim Drag (TTLTRMD) %***
fprintf(fid,'\n\n---- Total Trim Drag of Aircraft (Counts) ----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
TTLTRMDdisp=TTLTRMD; %***
TTLTRMDdisp(1,:)=MASTDRGdisp(1,:); %***
TTLTRMDdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(TTLTRMDdisp,1)) %***
fprintf(fid,'%10.2f',TTLTRMDdisp(n,:)); %***
fprintf(fid,'\n'); %***
end %***
% Rate Change of Total Drag w.r.t. AoA (CDALPHA) %***
fprintf(fid,'\n\n---- Rate Change of Total Drag w.r.t. Angle of Attack (***Units?)----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
CDALPHAdisp=CDALPHA; %***
CDALPHAdisp(1,:)=MASTDRGdisp(1,:); %***
CDALPHAdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(CDALPHAdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',CDALPHAdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',CDALPHAdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
% Compressibility Drag Matrix Adjusted for Wing Incremental Lift Effect (MASTDIZ) %***
fprintf(fid,'\n\n---- Compressibility Drag Matrix Adjusted for Wing Incremental Lift Effect (Counts)----\n'); %***
fprintf(fid,'Mach Number / Operating Lift Coefficient\n\n'); %***
MASTDIZdisp=MASTDIZ; %***
MASTDIZdisp(1,:)=MASTDRGdisp(1,:); %***
MASTDIZdisp(:,1)=MASTDRGdisp(:,1); %***
for n=1:1:(size(MASTDIZdisp,1)) %***
if n==1 %***
fprintf(fid,'%12.2f',MASTDIZdisp(n,:)); %***
else %***
fprintf(fid,'%12.4f',MASTDIZdisp(n,:)); %***
end %***
fprintf(fid,'\n'); %***
end %***
fprintf(fid,'\n\n*** End of File ***'); %***
fclose(fid); %***
disp(' ') %***
disp(' File written to:') %***
disp(strcat(strcat(pwd,'\'),strcat(fname,'-drgout.txt'))); %***
disp(' ') %***
op=0; %***
cd(settings.hdir) %***
%open 'dragout.txt' %***
%end %drgfile function %***
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
otherwise %***
return %***
end %***
end %texport function %***