College
College of Engineering (COE)
Date of Last Revision
2023-05-03 17:05:38
Major
Aerospace Systems Engineering
Honors Course
4900:497
Number of Credits
2
Degree Name
Bachelor of Science
Date of Expected Graduation
Spring 2020
Abstract
Using a finite-volume approach and ANSYS/FLUENT, supersonic flow over a 2-D ramp of varying angles is modeled. The computational results from this model will be used to further explore the design of supersonic diffusers used on military aircraft. Using grid capturing features and inflation layers, shockwave and boundary layer interactions will be observed as well as wave-associated pressure changes in supersonic turbulent flow. The Spalart-Allmaras single-equation model of turbulent flow will be used in all simulations to more accurately represent the phenomena that occur in such high-speed environments. The size of upstream zones and recirculation zones will be obtained through this model where applicable. Downstream zones of influence will be represented in terms of skin friction coefficient. Single-ramp data will be compared with double-ramp data to better understand how diffusers are modeled in industry for supersonic aircraft. This data will be the basis for the latter simulations representing internal compression and spike inlets. Inlet geometries are compared based on their stagnation pressure losses.
Research Sponsor
Alex Povitsky
First Reader
Scott Sawyer
Second Reader
Francis Loth
Honors Faculty Advisor
Nicholas Garafolo
Recommended Citation
Fulop, Lucas; Henry, Ian; Ruffner, Jordan; and McMullen, Anthony, "Supersonic Propulsion: Inlet Shock Wave/Boundary Layer Interaction in a Diffuser" (2020). Williams Honors College, Honors Research Projects. 1161.
https://ideaexchange.uakron.edu/honors_research_projects/1161