Av A PDk1k

The mass flow through a rocket nozzle is therefore proportional to the throat area At and the chamber (stagnation) pressure px \ it is also inversely proportional to the square root of T/W. and a function of the gas properties. For a supersonic nozzle the ratio between the throat and any downstream area at which a pressure px prevails can be expressed as a function of the pressure ratio and the ratio of specific heats, by using Eqs. 3-4, 3-16, 3-21, and 3-23, as follows:

Was this article helpful?

0 0
Project Management Made Easy

Project Management Made Easy

What you need to know about… Project Management Made Easy! Project management consists of more than just a large building project and can encompass small projects as well. No matter what the size of your project, you need to have some sort of project management. How you manage your project has everything to do with its outcome.

Get My Free Ebook

Post a comment