Calculating Thrust and Work for a Vinegar and Baking Soda Rocket

AI Thread Summary
The discussion focuses on a high school project where students design a rocket using acetic acid and baking soda to produce CO2 gas. The teacher has performed stoichiometric calculations and applied the ideal gas law to determine the pressure generated. The main challenge lies in calculating thrust and work done by the gas, with the teacher seeking simple equations for these calculations. Suggestions include using reaction mass like water or sodium acetate, as direct CO2 exhaust is deemed inefficient. The conversation emphasizes the importance of considering factors like nozzle area, density, and pressure differences in the calculations.
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I am a high school teacher attempting to give my students a project for designing a rocket powered by the chemical reaction between acetic acid and baking soda to produce CO2 gas.

I have done some simple calculations based on stoichiometric amounts of vinegar and acetic to produce a stoichiometric amount of CO2. I then have taken the moles of gas produced and solved for the pressure produced using the ideal gas law equation.

The calculations are attached in the Excel file.

Now I come to the troubling part. The students will be using a 2-L soda bottle as their rocket.

As the physics part of the project I would like to the students to calculate many things:

Fthrust and work done by the gas.

What are the simplest equations to use to calculate Fthrust and Work ?

I've attempted to make several equations which give me some very non-sensible results.
 

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Do you plan to use some reaction mass, like water? A direct CO2 exhaust is quite inefficient. There are several threads about rockets in the forums (at least one of them is in the "Similar Threads" list below).
 
I think the products, sodium acetate and water, or simply sodium acetate solution can act as the reaction mass right?
 
I'm not sure if that is a good idea...
 
The reaction mass is the whole thing yes.
 
I just need a simple equation for the force of Thrust
 
##F=\frac{dm}{dt}v \approx \rho A v^2## where A is the area of the nozzle, rho is the density and v is the velocity there. Neglecting compression and inefficiencies, ##\rho v^2 = 2 \Delta p## with the pressure difference inside/outside. For gas as reaction mass (bad), compression is relevant, of course, so it might need a better analysis.
 
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