Abstract
Supersonic retro-propulsion (SRP) is defined as rocket propulsion used to decelerate aerospace vehicles at supersonic speed. SRP is often used as a method of high-speed deceleration on space vehicles. The main method of propulsion used in the application of SRP is rocket propulsion. Rocket engine thrust and performance changes with altitude and expansion ratio. Changing altitudes across the trajectory of a rocket affect how the exhaust plume shock waves expand. Being able to identify how different expansion ratios affect the exhaust plume flow fields would provide useful data on how SRP performance can be predicted. This research projects aims at developing a computational model for existing physical test data on SRP and extrapolating data from the model to assess how SRP would perform with different nozzle expansion ratios.
Thesis Completion
2022
Semester
Spring
Thesis Chair/Advisor
Kinzel, Michael
Degree
Bachelor Science in Aerospace Engineering (B.S.A.E.)
College
College of Engineering and Computer Science
Department
Mechanical and Aerospace Engineering
Degree Program
Aerospace Engineering
Language
English
Access Status
Open Access
Release Date
5-1-2022
Recommended Citation
Montoya, Gonzalo, "Analysis of Nozzle Expansion Characteristics in Supersonic Retro-Propulsion" (2022). Honors Undergraduate Theses. 1177.
https://stars.library.ucf.edu/honorstheses/1177