
Nozzle Design and Automation
Hello everyone! I am an aerospace engineering student with an IT background and I am developing an experimental rocket engine with which I want to make various experiments changing propellant composition. (Like different OFs).
From what I can grasp, changing your propellant will affect your nozzle design.
Now, I know you can use numerical methods, but from what I can grasp of Rocket Propulsion Elements, ninth edition chapter 3, I get that you could define chamber to throat (so, both diameters) without changing much and you could easily get your exit area to throat area relation using a tool like CEA.
Now, this leaves me with some questions:
- How do you define Throat area? I am calculating it from a static chamber area which is constrained by the design, using a chamber to throat area ratio of 4.5. A bit higher than the 3.5 from the 3-2 table. Is this correct? Should I take other things into account?
From what I understand a conical throat could be completely "straight", with no curves, is this correct?
I am using formulas to get values like cone length and other things, is this correct or I better get into numeric methods straight away?
How viable is to automate this process? Are there any tools that do it? In case there aren't, why? Is it plain impossible, too hard or the complex of the project doesn't outweigh the benefits?
Thanks for reading and sorry if I missed something.