Write a code in any programming language $($C$,$ C$++,$ Fortran, MATLAB, Python, etc.$)$ to

determine thrust and TSFC for an ideal ramjet with a given combustor total temperature as a

function of flight Mach number and altitude. Use the attached atmospheric model to determine

ambient conditions at a given altitude. Use a heating value for the fuel of $18,000BT\frac{U}{l}{b}_m$ and a

value of $c_p$ of $0\mathrm{.}24BT\frac{U}{l{b}_{m}R}.$ You may use any programming environment that you wish. You are

encouraged to use Fortran or C but Matlab, Visual Basic or any other environment is acceptable.

Turn in your working code to the teaching assistant.

A$.$ For a combustor total temperature of $4500R$ and a nozzle throat diameter of $1$ ft $,$ plot

the thrust and TSFC for a constant Mach number of $3$ for altitudes ranging from $20,000$ ft

to $100,000ft.$

B$.$ For a fixed altitude of $50,000$ ft and a combustor total temperature of $4500R,$

plot thrust and TSFC for Mach numbers ranging from $0$ to $8.$

$**$Please give code in MATLAB thanks$**$