Integrated Rocket Ramjet (IRR): Team Rocket

The goal is to design and model an Integrated Rocket Ramjet (IRR) engine design that will transition from the solid rocket phase to the ramjet phase after reaching the designed speed by means of a transitional nose cone device. The transitional nose cone will also serve as an inlet optimization tool to maximize exit conditions for optimal thrust.

Background
This design project requires an understanding of compressible flow also known as gas dynamics and supersonic engine designs. There are many sources available for reference and understanding of compressible flow dynamics and some links below in the references section.