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
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.