Keith Koenig, Keith
Date of Degree
Graduate Thesis - Open Access
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.
Gould, Cedric O, "Design of an aerospike nozzle for a hybrid rocket" (2008). Theses and Dissertations MSU. 1305.