Matlab code using ode45 difficulty

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SUMMARY

The forum discussion centers on troubleshooting a MATLAB code utilizing the ode45 function to model a fall over varying altitudes. The user encounters persistent errors while executing the code, which includes a custom ODE function 'fallode' that calculates altitude and vertical velocity. Key suggestions from other users include posting specific error messages for better assistance and utilizing 'fprintf' for outputting results to the display. Additionally, formatting the code with [code] tags is recommended to enhance readability.

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  • Familiarity with MATLAB programming and syntax
  • Understanding of ordinary differential equations (ODEs)
  • Knowledge of atmospheric physics, specifically temperature and density calculations
  • Experience with debugging techniques in MATLAB
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  • Learn how to effectively use MATLAB's 'ode45' function for solving ODEs
  • Research MATLAB error handling and debugging techniques
  • Explore the use of 'fprintf' for formatted output in MATLAB
  • Study the US standard atmosphere model for accurate altitude-related calculations
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This discussion is beneficial for MATLAB users, students studying atmospheric physics, and anyone interested in numerical methods for solving ODEs.

zfolwick
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Homework Statement



I've been trying to get this code to work:
ode45(@(t,y) fallode(t,y,B), [0, tmax], [31330, 0])

Homework Equations



function dy = fallode(t, y, B)
% ODE function to model a fall over a large range of
% altitudes, reaching up to high subsonic Mach numbers.
% y(1) is altitude, y(2) is vertical velocity (positive up).
% Variation of gravity with altitude is ignored.
g = 9.8; % Earth gravity, m/s^2
R = 287; % Specific gas constant of air, J/kg*K
gamma = 1.4; % Ratio of specific heats of air, dimensionless
[T, rho] = atmos(y(1));
dy(1,1) = y(2);
dy(2,1) = -g + rho*B*y(2)^2/(2*sqrt(1 - y(2)^2/(gamma*R*T)));

--------------

function [T, rho] = atmos(ha)
% Calculate the temperature and density at a given absolute
% altitude ha in the US standard atmosphere model (lowest
% three layers only)
re = 6378.e3; % Radius of Earth, mean equatorial, meters
% Geopotential altitude
h = re*ha/(re + ha);
R = 287; % Specific gas constant for air, J/(kg*K)
g0 = 9.8; % Earth surface gravity, m/s^2
hbreak1 = 11e3; % Altitude of break between 1st and 2nd layers in model
hbreak2 = 25e3; % Altitude of break between 2nd and 3rd layers in model
for ii = 1:length(ha)
if (h <= hbreak1)
a = -6.5e-3; % Temperature lapse rate in troposphere, K/m
rho1 = 1.225; % Surface air density in standard atm. model, kg/m^3
T1 = 288.16; % Surface temperature in standard atm. model, K
T(ii) = T1 + a*h(ii); % Temperature at altitude, K
rho(ii) = rho1*(T(ii)/T1)^(-g0/(a*R)-1); % Density at altitude, kg/m^3
elseif (h <= hbreak2)
T(ii) = 216.66; % Temperature between 11km and 25km altitude, K
rhos = 0.3642; % Density at 11km altitude, kg/m^3
rho(ii) = rhos*exp(-(h(ii) - hbreak1)*g0/(R*T)); % Density at altitude, kg/m^3
else
4a = 3e-3; % Temperature lapse rate in stratosphere, K/m
rho1 = 0.0401; % Density at 25km altitude, kg/m^3
T1 = 216.66; % Temperature at 25 km altitude, K
T(ii) = T1 + a*(h(ii) - hbreak2); % Temperature at altitude, K
rho(ii) = rho1*(T(ii)/T1)^(-g0/(a*R)-1); % Density at altitude, kg/m^3
end
end


The Attempt at a Solution



I've gotten nothing but errors. Any help troubleshooting would be appreciated.
 
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zfolwick said:
I've gotten nothing but errors.

Don't you think it would be helpful if you post the errors?
 
Last edited:
Nylex said:
Don't you think it would be helpful if you post the errors?

I concur, also why don't you just use fprintf to output to the display screen your results with units instead of using notes that don't get outputted to the display screen?
 
It also wouldn't hurt to use
Code:
 tags to preserve the indentation, to help readability.
 

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