Altitude Compensating Ringed Nozzle

The increased focus on supersonic and hypersonic flows necessitates methods to study such flows in laboratory-based facilities, thus motivating researchers to find effective, efficient, and affordable methods to produce them in laboratories. It is desirable for the rocket nozzles to operate efficiently at different altitudes, which made the Altitude Compensating Nozzles emerge as a solution. In this work, we propose a new design for such nozzles, namely, the ringed nozzle. The proposed nozzle consists of a stack of parallel rings that serve as a nozzle with bleeding slots. This design can be utilised to obtain different exit Mach numbers and attain the desired performance according to the pressure ratio, serving as an Altitude Compensating Nozzle. The stack of rings might be altered to tailor nozzle shape and area ratio corresponding to the nozzle requirement. The nozzle is analysed from an engineering perspective by comparing the thrust coefficient and specific impulse, and the numerical simulations show promising results.