Thread: Problem Transitioning Equations With "if" Statements

PLEASE HELP!!
So i have an assignment i need to do for school, and i have hit an intriguing obstacle. It happens to be the first matlab obstacle i havent been able to surpass.
INFORMATION-So, when the you look at the earth's atmosphere under standard temperature and pressure, you can find out the values and ratios of temperature, pressure, and density values with a lone input of altitude.
Pressure and density are determined by calculating temperature which is calculated by altitude. Temperature goes through a series of gradient (sloped temperature change with altitude) and isothermal (no temperature change with altitude) sections.
MY PROBLEM-When switching from a gradient section (0m<altitude<11000m) to an isothermal section (11000<=Altitude<25000) within an group of if-statements, my matlab presents an error of "??? Reference to a cleared variable Prat." where Prat (Pressure Ratio) is a calculated function in "if 0m<altitude<11000" and "elseif (11000<=Altitude<25000)"
OTHER TESTS- the program runs flawlessly when the altitude stays within one single if/elseif statement, but any transition between altitude ranges presents this error. So, i'm pretty confident that there isn't a simple error in coding.
QUESTION- how do i transition between altitude ranges?? for example, entering altitude=[0:10000] or altitude=[11000:24000] works fine, but entering altitude=[10999:11000] wont work

Originally Posted by beanyo

PLEASE HELP!!
So i have an assignment i need to do for school, and i have hit an intriguing obstacle. It happens to be the first matlab obstacle i havent been able to surpass.
INFORMATION-So, when the you look at the earth's atmosphere under standard temperature and pressure, you can find out the values and ratios of temperature, pressure, and density values with a lone input of altitude.
Pressure and density are determined by calculating temperature which is calculated by altitude. Temperature goes through a series of gradient (sloped temperature change with altitude) and isothermal (no temperature change with altitude) sections.
MY PROBLEM-When switching from a gradient section (0m<altitude<11000m) to an isothermal section (11000<=Altitude<25000) within an group of if-statements, my matlab presents an error of "??? Reference to a cleared variable Prat." where Prat (Pressure Ratio) is a calculated function in "if 0m<altitude<11000" and "elseif (11000<=Altitude<25000)"
OTHER TESTS- the program runs flawlessly when the altitude stays within one single if/elseif statement, but any transition between altitude ranges presents this error. So, i'm pretty confident that there isn't a simple error in coding.
QUESTION- how do i transition between altitude ranges?? for example, entering altitude=[0:10000] or altitude=[11000:24000] works fine, but entering altitude=[10999:11000] wont work

Can you post the actual code fragment giving the message

Also consider setting some break points and running the code in the debugger stopping at appropriate points and examining the relevant variables.

CB

CB

Code:

%Goal: Calculate Pressure, Pressure Ratio, Density, Density Ratio,
%Temperature, and Temperature Ratio based on an Altitude input.
    
%This program operates using air as a medium.  The Gas Constant, density,
%and atmospheric pressure are constant and refer to standard atmospheric temperature
%and pressure.  Gravitational pull is also considered constant.

clear,clc

alt=input('Enter your altitude:  ');
go=9.8; %m/s^2
R=287.05; %J/K mol                     
P1=101325; %N/,^2
rho1=1.225; %kg/m^3
T1=288.16; %K
h1=0;
a=[-6.5*10^-3 3*10^-3 -4.5*10^-3 4*10^3];
aeng=a.*.54864;

i=1;

while i<=length(alt)

if             alt==0
            T(i)=288.6 %K
            Prat(i)=1
            rhorat(i)=1
    
        elseif alt>=0 & alt<11000
            a=a(1); %K/m
            T(i)=T1+a.*(alt(i)-h1)
            Prat(i)=(T(i)./T1).^-(go./(a.*R))            
            rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
                        
        elseif alt>=11000 & alt<25000
            T(i)=216.66 %K
            Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            rhorat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            
        elseif alt>=25000 & alt<47000
            a=a(2); %K/m
            T(i)=T1+a.*(alt(i)-h1)
            Prat(i)=(T(i)./T1).^-(go./(a.*R))
            rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
            
        elseif alt>=47000 &alt<53000
            T(i)=282.66 %K
            Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            rhorat(i)=Prat(i+1)
            
        elseif alt>=53000 & alt<79000
            a=a(3); %K/m
            T(i)=T1+a.*(alt(i+1)-h1)
            Prat(i)=(T(i)./T1).^-(go./(a.*R))
            rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
            
        elseif alt>=79000 & alt<90000
            T(i)=165.66 %K
            Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            rhorat(i)=Prat(i)
            
        elseif alt>=90000 & alt<105000
            a=a(1); %K/m
            T(i)=T1+a.*(alt(i)-h1)
            Prat(i)=(T(i)./T1).^-(go./(a.*R))
            rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
            
        elseif alt==105000
            T(i)=225.66; %K
            Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            rhorat(i)=Prat(i+1)
            
        elseif alt<0 | alt>105000
            fprintf('Error: This code only evaluates outputs within a range of 0-105000 meters\n')
            
end

P=P1.*Prat
rho=rho1.*rhorat
sigma=rho./rho1

i=i+1;

end

Originally Posted by beanyo

Code:

%Goal: Calculate Pressure, Pressure Ratio, Density, Density Ratio,
%Temperature, and Temperature Ratio based on an Altitude input.
 
%This program operates using air as a medium.  The Gas Constant, density,
%and atmospheric pressure are constant and refer to standard atmospheric temperature
%and pressure.  Gravitational pull is also considered constant.
 
clear,clc
 
alt=input('Enter your altitude:  ');
go=9.8; %m/s^2
R=287.05; %J/K mol                     
P1=101325; %N/,^2
rho1=1.225; %kg/m^3
T1=288.16; %K
h1=0;
a=[-6.5*10^-3 3*10^-3 -4.5*10^-3 4*10^3];
aeng=a.*.54864;
 
i=1;
 
while i<=length(alt)
 
if             alt==0
            T(i)=288.6 %K
            Prat(i)=1
            rhorat(i)=1
 
        elseif alt>=0 & alt<11000
            a=a(1); %K/m
            T(i)=T1+a.*(alt(i)-h1)
            Prat(i)=(T(i)./T1).^-(go./(a.*R))            
            rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
 
        elseif alt>=11000 & alt<25000
            T(i)=216.66 %K
            Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            rhorat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
 
        elseif alt>=25000 & alt<47000
            a=a(2); %K/m
            T(i)=T1+a.*(alt(i)-h1)
            Prat(i)=(T(i)./T1).^-(go./(a.*R))
            rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
 
        elseif alt>=47000 &alt<53000
            T(i)=282.66 %K
            Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            rhorat(i)=Prat(i+1)
 
        elseif alt>=53000 & alt<79000
            a=a(3); %K/m
            T(i)=T1+a.*(alt(i+1)-h1)
            Prat(i)=(T(i)./T1).^-(go./(a.*R))
            rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
 
        elseif alt>=79000 & alt<90000
            T(i)=165.66 %K
            Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            rhorat(i)=Prat(i)
 
        elseif alt>=90000 & alt<105000
            a=a(1); %K/m
            T(i)=T1+a.*(alt(i)-h1)
            Prat(i)=(T(i)./T1).^-(go./(a.*R))
            rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
 
        elseif alt==105000
            T(i)=225.66; %K
            Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
            rhorat(i)=Prat(i+1)
 
        elseif alt<0 | alt>105000
            fprintf('Error: This code only evaluates outputs within a range of 0-105000 meters\n')
 
end
 
P=P1.*Prat
rho=rho1.*rhorat
sigma=rho./rho1
 
i=i+1;
 
end

If alt=[100,2000] what do you think

Code:

if alt==0
   x=x+1
elseif (alt>0) & (alt<1000)
   x=x+2
end

does?

Also the line:

rhorat(i)=Prat(i+1)

appears to use Prat(i+1) before its calculated.

Other comments: These are not show stoppers, but they are good practice:

1. Do not use a while loop when you know the trip count around a loop. use a for loop instead.
2. Declare arrays of known dimensions, do not let Matlab rearrange memory every time you access a different element.

Originally Posted by CaptainBlack

If alt=[100,2000] what do you think

Code:

if alt==0
   x=x+1
elseif (alt>0) & (alt<1000)
   x=x+2
end

does?

Also the line:

rhorat(i)=Prat(i+1)

appears to use Prat(i+1) before its calculated.

Other comments: These are not show stoppers, but they are good practice:

1. Do not use a while loop when you know the trip count around a loop. use a for loop instead.
2. Declare arrays of known dimensions, do not let Matlab rearrange memory every time you access a different element.

I guess I've been using some offbeat logic on this code then, I guess

I was under the impression I could use two separate equations for one variable so long as they were indexed correctly (which, somehow my matlab wasn't doing outside of a loop in an earlier version of my code [obviously due to some other error])
I assume you are implying that my if/elseif setup will just cause my Prat from the first elseif to try and overwrite the Prat from the second elseif? Sorry I need the clarification; it seems logical it just want intuitive for me :/
also, good call on the Prat(i+1)--it was an earlier (and incorrect) indexing I was using before.... I guess I'm tripping up all over the place :/. I hope I'm just rusty
what advantages does a for loop have over a while loop?
And, if you don't mind, do you know of any way I could successfully set up what I was trying to do? Since the idea is to plot the outputs at the end, I suppose I could break up the different pressure and temperature sections into different equations and stick them together at the end
Thanks a lot for the advice so far!! I really appreciate it!

Originally Posted by beanyo

I guess I've been using some offbeat logic on this code then, I guess

I was under the impression I could use two separate equations for one variable so long as they were indexed correctly (which, somehow my matlab wasn't doing outside of a loop in an earlier version of my code [obviously due to some other error])
I assume you are implying that my if/elseif setup will just cause my Prat from the first elseif to try and overwrite the Prat from the second elseif? Sorry I need the clarification; it seems logical it just want intuitive for me :/
also, good call on the Prat(i+1)--it was an earlier (and incorrect) indexing I was using before.... I guess I'm tripping up all over the place :/. I hope I'm just rusty
what advantages does a for loop have over a while loop?
And, if you don't mind, do you know of any way I could successfully set up what I was trying to do? Since the idea is to plot the outputs at the end, I suppose I could break up the different pressure and temperature sections into different equations and stick them together at the end
Thanks a lot for the advice so far!! I really appreciate it!

When you apply a logic test to a vector or array you get a vector of results. If it is in an if structure it appears to be interpreted as:

if (any(alt==0))

You should not be applying a logical test to a vector in an if statement, you should be applying it to a specific element like:

if alt(i)==0

CB

Originally Posted by CaptainBlack

When you apply a logic test to a vector or array you get a vector of results. If it is in an if structure it appears to be interpreted as:

if (any(alt==0))

You should not be applying a logical test to a vector in an if statement, you should be applying it to a specific element like:

if alt(i)==0

CB

You, sir, are a gentleman and a scholar.
I can't express how awesome i felt when the code started working right.
I completely understand where you're coming from now, so thanks a ton for the information. It broadened my insight.

Anyway, there is still one roadblock I'm hitting, that I can't seem to figure out. Its an indexing error whenever i run between 25000 and 47000 meters. I've seen the error before, but i cant seem to get rid of it this time :/
"??? Index exceeds matrix dimensions"

Here's my code as of now (and no, i didn't ignore you before; but for the interest of time i haven't changed it to a for loop yet)


%Goal: Calculate Pressure, Pressure Ratio, Density, Density Ratio,
%Temperature, and Temperature Ratio based on an Altitude input.

%This program operates using air as a medium. The Gas Constant, density,
%and atmospheric pressure are constant and refer to standard atmospheric temperature
%and pressure. Gravitational pull is also considered constant.

clear,clc

alt=input('Enter your altitude: ');
go=9.8; %m/s^2
R=287.05; %J/K mol
P1=101325; %N/,^2
rho1=1.225; %kg/m^3
T1=288.16; %K
h1=0;
a=[-6.5*10^-3 3*10^-3 -4.5*10^-3 4*10^3];
aeng=a.*.54864;
ao=0;

i=1;

while i<=length(alt)

if alt(i)==0
T(i)=288.6 %K
Prat(i)=1
rhorat(i)=1

elseif alt(i)>=0 & alt(i)<11000
a=a(1); %K/m
T(i)=T1+a.*(alt(i)-h1)
Prat(i)=(T(i)./T1).^-(go./(a.*R))
rhorat(i)=exp(1).^-(go./(a.*T(i))+1)

elseif alt(i)>=11000 & alt(i)<25000
T(i)=216.66+ao.*(alt(i)-h1) %K
Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
rhorat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))

elseif alt(i)>=25000 & alt(i)<=47000
a=a(2); %K/m
T(i)=T1+a.*(alt(i)-h1)
Prat(i)=(T(i)./T1).^-(go./(a.*R))
rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
end

P(i)=P1.*Prat(i)
rho(i)=rho1.*rhorat(i)
sigma(i)=rho(i)./rho1

i=i+1

end

Originally Posted by beanyo

You, sir, are a gentleman and a scholar.
I can't express how awesome i felt when the code started working right.
I completely understand where you're coming from now, so thanks a ton for the information. It broadened my insight.

Anyway, there is still one roadblock I'm hitting, that I can't seem to figure out. Its an indexing error whenever i run between 25000 and 47000 meters. I've seen the error before, but i cant seem to get rid of it this time :/
"??? Index exceeds matrix dimensions"

Here's my code as of now (and no, i didn't ignore you before; but for the interest of time i haven't changed it to a for loop yet)


%Goal: Calculate Pressure, Pressure Ratio, Density, Density Ratio,
%Temperature, and Temperature Ratio based on an Altitude input.

%This program operates using air as a medium. The Gas Constant, density,
%and atmospheric pressure are constant and refer to standard atmospheric temperature
%and pressure. Gravitational pull is also considered constant.

clear,clc

alt=input('Enter your altitude: ');
go=9.8; %m/s^2
R=287.05; %J/K mol
P1=101325; %N/,^2
rho1=1.225; %kg/m^3
T1=288.16; %K
h1=0;
a=[-6.5*10^-3 3*10^-3 -4.5*10^-3 4*10^3];
aeng=a.*.54864;
ao=0;

i=1;

while i<=length(alt)

if alt(i)==0
T(i)=288.6 %K
Prat(i)=1
rhorat(i)=1

elseif alt(i)>=0 & alt(i)<11000
a=a(1); %K/m
T(i)=T1+a.*(alt(i)-h1)
Prat(i)=(T(i)./T1).^-(go./(a.*R))
rhorat(i)=exp(1).^-(go./(a.*T(i))+1)

elseif alt(i)>=11000 & alt(i)<25000
T(i)=216.66+ao.*(alt(i)-h1) %K
Prat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))
rhorat(i)=exp(1).^-(go./(R.*T(i)).*(alt(i)-h1))

elseif alt(i)>=25000 & alt(i)<=47000
a=a(2); %K/m
T(i)=T1+a.*(alt(i)-h1)
Prat(i)=(T(i)./T1).^-(go./(a.*R))
rhorat(i)=exp(1).^-(go./(a.*T(i))+1)
end

P(i)=P1.*Prat(i)
rho(i)=rho1.*rhorat(i)
sigma(i)=rho(i)./rho1

i=i+1

end

don't do a=a(1) or a=a(2), since they both retype a as a scallar.

CB

Actually, my bad. I got it. It had something to do with the way i set up my equation.

But seriously, you are a savior
Thanks a lot once again.