Design and Testing of a Ramjet as a Second Stage for Small Scale Rocket Models

Airbreathing propulsion technologies play a crucial role in both civil and military aerospace applications due to their high efficiency in atmospheric flight. Unlike traditional rocket propulsion, which relies on onboard oxidizers, a ramjet utilizes atmospheric oxygen, potentially improving overall system efficiency and reducing launch weight. The proposed ramjet is optimized for a cruise Mach, withdesignparametersincludinginlet rampangles, pressure losses, and combustion efficiency carefully selected to maximize performance. A detailed analysis is conducted on the air inlet system, combustion chamber geometry, and nozzle configuration to ensure stable operation across the expected flight envelope. Special attention is given to the selection of fuel and ignition strategies to guarantee reliable startup and sustained combustion under varying f low conditions. Following the conceptual and computational design phase, a scaled prototype was fabricated using high-resolution 3D printing. Experimental testing was conducted in a controlled environment to evaluate key performance parameters, with a particular focus on new configuration rocket model stability and overall thrust production. The outcomes of this research will provide valuable insights into the feasibility of integrating ramjet technology into small-scale orbital launch systems, potentially offering a cost-effective and efficient alternative to conventional rocket staging strategies.