Design of an aerospike nozzle for a hybrid rocket

Author

Cedric O. Gould

Issuing Body

Mississippi State University

Advisor

Keith Koenig, Keith

Committee Member

Olsen, Gregory

Committee Member

Cinnella, Pasquale

Date of Degree

8-9-2008

Document Type

Graduate Thesis - Open Access

Major

Aerospace Engineering

Degree Name

Master of Science (M.S.)

College

James Worth Bagley College of Engineering

Department

Department of Aerospace Engineering

Abstract

This document describes the design of an axisymmetric aerospike nozzle to replace the conical converging-diverging nozzle of a commercially available hybrid rocket motor. The planar method of characteristics is used with isentropic flow assumptions to design the nozzle wall. Axisymmetric adjustments are made with quasi-one-dimensional flow approximations. Computational Fluid Dynamics (CFD) simulations verify these assumptions, and illustrate viscous effects within the flow. Nozzle truncations are also investigated. Development of a hybrid-rocket-specific data acquisition system is also detailed.

URI

https://hdl.handle.net/11668/15256

Recommended Citation

Gould, Cedric O., "Design of an aerospike nozzle for a hybrid rocket" (2008). Theses and Dissertations. 1305.
https://scholarsjunction.msstate.edu/td/1305