• Badhri Kumaravel
• Nikhil Gangamkote
• Deepak Kumar Srinivasan
• Vishnu Kolanjimani

The Aero-Converged-Spike Nozzle presents a hybrid propulsion system that integrates the Convergent-Divergent (CD) Nozzle and the Aerospike Nozzle to optimize supersonic flow expansion, enhance thrust efficiency, and improve altitude adaptability. This design overcomes the limitations of conventional nozzles by combining the shock-free expansion of CD nozzles with the altitude-compensating characteristics of aerospike nozzles, resulting in superior aerodynamic performance.The nozzle geometry was formulated using the Method of Characteristics (MOC) in MATLAB, generating a precise supersonic contour. A 3D CAD model was developed in CATIA V5, and Computational Fluid Dynamics (CFD) simulations were performed in ANSYS Fluent to analyze pressure, velocity, and temperature distributions under operating conditions of 1 MPa chamber pressure and 1350 K combustion temperature.Simulation results confirm enhanced flow stability, with optimized supersonic expansion and reduced shock wave interactions. The pressure contours demonstrate effective altitude compensation, while velocity distributions indicate efficient kinetic energy conversion into thrust. Additionally, the temperature profiles reveal a significant reduction in aerothermal heating at the spike base, improving structural integrity and thermal resistance.Compared to conventional CD and aerospike nozzles, this hybrid design exhibits higher thrust efficiency, minimized energy losses, and extended operational lifespan, making it a promising advancement for next-generation aerospace propulsion systems.

Hybrid Nozzle, Aero-Converged-Spike Nozzle, Rocket Propulsion, Supersonic Flow, Thrust Optimization

"NUMERICAL INVESTIGATION APPROACH – COMPUTATIONAL FLUID DYNAMICS ON AERO-CONVERGED-SPIKE ROCKET NOZZLE", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.12, Issue 3, page no.h26-h38, March-2025, Available :http://www.jetir.org/papers/JETIR2503704.pdf

"NUMERICAL INVESTIGATION APPROACH – COMPUTATIONAL FLUID DYNAMICS ON AERO-CONVERGED-SPIKE ROCKET NOZZLE", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.12, Issue 3, page no. pph26-h38, March-2025, Available at : http://www.jetir.org/papers/JETIR2503704.pdf