MATLAB code for solid fuel rocket motor nozzle design

E= 67%Modulus of elasticity

K=1.17 %Adiabatic index of combustion products

Pk =5Mpa% Combustion chamber pressure

pa= 0.06 mpa% Nozzle outlet pressure

a2=a1=0.05m% The length of the conical sections forming the nozzle

θ_m=25% Opening angle of the nozzle

θ_a=8% The angle at the exit of the nozzle

t=70 s% Working time

F=240KN% thrust

ρ =1750kg/m^3% fuel density

R =310 KJ/Kg.k %Gas constant

T=3066k % Fuel combustion temperature

ISP=2350m/s % special impulse

Daniel, I believe that could work. The primary feature I am looking to utilize this for is to generate web components from Figma documents. The workflow that I would like would be to capture a screenshot and then selecting from an existing prompt to generate the web component code. I came across another approach from the developer of the Beam app that appears to be similar.

Thank you for your hard work on this feature. I appreciate it and I am eager to use it once you release it.

Hey Travis, would this work for you? https://twitter.com/daniel_nguyenx/status/1723617938400510366