Propellant Analysis

Choose a liquid bipropellant, solid propellant formulation, or hybrid combination of your

choice. You will conduct analysis using a chemical equilibrium code of your choice $($recommend

NASA CEA$).$

Part A

Choose a single equivalence ratio and calculate Isp, c$*,$ adiabatic flame temperature $($in

chamber$),$ CF $,$ temperature in the throat and exit of nozzle, as well as composition of the gases

$($those with mole fractions greater than $0\mathrm{.}1)$ in both locations $($chamber$,$ throat$).$ Choose

$$Infinite area$$ with both $$equilibrium$$ and $$frozen$$ checked. Input a chamber pressure of your

choice. Report and explain the differences between the two results. Which one is more

realistic? How do you expect these values to change $($if any change$)$ in practice compared to

theory? Explain why.

Part B

Repeat the calculations in chamber, throat, and exit locations with realistic chamber pressure,

expansion ratio, etc. as well as vary the equivalence ratio $($you will look at these quantities as a

function of equivalence ratio$).$

$1.$ Plot all the quantities above versus equivalence ratio.

$2.$ What trends do you observe? Explain reasons behind those trends.

$3.$ Do you notice any trends between the variables calculated $($e$.$g$.,$ does an increase in one

correspond to an increase in another$)?$ Provide explanations for those trends.

$4.$ Which equivalence ratio would you choose for your rocket $($if you were building one$)$

and why? Again, provide explanations and justifications.

Part C

Take the equivalence ratio you choose in last portion of Part A and now vary the chamber

pressure between $10$ atm and $500$ atm.

$1.$ Explain all the trends you see.

$2.$ What are the pros and cons of using a low or high pressure? Explain it in terms of

thermochemistry, but also other aspects you may need to consider when designing a

rocket.