Use the equations developed $($see Slide $21)$ to write a computer program to perform a Ramjet Analysis to plot

TSFC and Isp as a function of different parameters $-$ you can use Excel, Matlab, Python or any other programming

language of your choice. Label the axis and Label the plots. Explain briefly what you see in the plots.

Plot TSFC and Isp vs M$,$ from $1\mathrm{.}5$ to $4\mathrm{.}5$ in steps of $0\mathrm{.}25$

Set all inefficiencies to $1.$

Incoming static temperature $=220K.$

T$04($Tmax$)=3400K$

Perfectly expanded nozzle, so pa$=$pe

Heat of combustion, $Qr=45M\frac{J}{k}\frac{g}{K}$

$Cp=1005\frac{J}{k}\frac{g}{K},R=287\frac{J}{k}\frac{g}{K},=1\mathrm{.}4$

Plot TSFC and Isp vs $T_{04}($i$.$e$.,$ maximum allowable temperature at the exit of the combustor$),$ vary from

$1000$K to $4000$ K in steps of $200$ K $.$

Set all inefficiencies to $1.$

Incoming static temperature $=220K.$

Perfectly expanded nozzle, so pa$=$pe

Heat of combustion, $Qr=45M\frac{J}{k}\frac{g}{K}$

$Cp=1005\frac{J}{k}\frac{g}{K},R=287\frac{J}{k}\frac{g}{K},=1\mathrm{.}4$

incoming Mach number of $3$

Plot TSFC and Isp vs $r_d,$ and ${}_b$ individually by varying them one at a time from $0\mathrm{.}6$ to $1($in steps of $0\mathrm{.}1).$

Hold the other inefficiencies at $1.$ For example, if you are looking at the effect of $r_d,$ make all other at $1$

and vary $r_d$ from $0\mathrm{.}6$ to $1.$

incoming Mach number of $3.$

perfectly expanded nozzle, so pa$=$pe

T$04($Tmax$)<mtext></mtext><mn>3</mn><mn>4</mn><mn>0</mn><mn>0</mn>$K

Incoming static temperature, $220$K

Heat of combustion, $Qr=45M\frac{J}{k}\frac{g}{K}$

$Cp=1005\frac{J}{k}\frac{g}{K},R=287\frac{J}{k}\frac{g}{K},g=1\mathrm{.}4$