NUMERICAL SIMULATION AND OPTIMIZATION OF HIGH PERFORMANCE SUPERSONIC NOZZLE AT DIFFERENT CONICAL ANGLES

The Principle purpose of a nozzle is to accelerate the flow to higher exit velocities.The fluid acceleration is based on the design criteria and characteristics.To achieve good performance characteristics with minimum energy losses a nozzle must satisfy all the design requirements at all operating conditions.This is possible only when the nozzle theory is assumed to be isentropic irrespective of the changes in pressure, temperature and density which is generally caused due to formation of a Shock Wave.The thesis focuses on the design, development and optimization of a Supersonic Convergent-Divergent Nozzle where the analytical results are validated using theory calculations.The simulation work is carried out for CD Nozzles with different angles of divergence keeping the other inputs fixed.The objective of the proposed thesis is to show the best Expansion ratio, Nozzle Pressure ratio (NPR) and Nozzle Area Ratio(NAR) where the thrust obtained by the supersonic nozzle is maximum.The simulation is then repeated for expansion gas the results of which are later compared with standard air to show which possesses better performance characteristics.The Nozzle design chosen is based upon existing literature studies.