Abstract Title

CFD Study in Compound-Compressible Flow Nozzles for Rocket Thrust Augmentation

Faculty Mentor Name

Shigeo Hayashibara

Format Preference

Poster

Abstract

A compound-compressible flow nozzle can be used to augment the thrust generated by a rocket engine by using the rocket engine plume to entrain an air flow. The rocket engine plume and air flow mixes together within the nozzle to create an exhaust flow that generates additional thrust. The objective of this Computational Fluid Dynamics (CFD) study is to simulate the turbulent mixing of the rocket engine plume with the entrained air flow within a compound-compressible flow nozzle. Experimental data collected from tests of a rocket engine and compound-compressible flow nozzle system, which was designed and fabricated by the Ignite Mercury Propulsion Team, was used to create and validate a quasi-3D CFD simulation of the engine and nozzle system. The study provides insight on how a compound-compressible flow nozzle is used to augment the thrust generated by a rocket engine, and how the nozzle should be designed to minimize total pressure losses within the engine and nozzle system.

Location

AC1-ATRIUM

Start Date

3-31-2017 11:00 AM

End Date

3-31-2017 3:00 PM

Share

COinS
 
Mar 31st, 11:00 AM Mar 31st, 3:00 PM

CFD Study in Compound-Compressible Flow Nozzles for Rocket Thrust Augmentation

AC1-ATRIUM

A compound-compressible flow nozzle can be used to augment the thrust generated by a rocket engine by using the rocket engine plume to entrain an air flow. The rocket engine plume and air flow mixes together within the nozzle to create an exhaust flow that generates additional thrust. The objective of this Computational Fluid Dynamics (CFD) study is to simulate the turbulent mixing of the rocket engine plume with the entrained air flow within a compound-compressible flow nozzle. Experimental data collected from tests of a rocket engine and compound-compressible flow nozzle system, which was designed and fabricated by the Ignite Mercury Propulsion Team, was used to create and validate a quasi-3D CFD simulation of the engine and nozzle system. The study provides insight on how a compound-compressible flow nozzle is used to augment the thrust generated by a rocket engine, and how the nozzle should be designed to minimize total pressure losses within the engine and nozzle system.