College

College of Engineering (COE)

Date of Last Revision

2020-05-07 13:10:05

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

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