Date of Award

3-1-2018

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Darrell S. Crowe, PhD.

Abstract

Shock-wave/boundary layer interactions (SWBLI) produce undesirable dynamic loads and separated unsteady flows, adversely impacting the performance and structural integrity of supersonic vehicles. Computational fluid dynamics (CFD) is a successful tool in experimental planning and shows promise as a critical tool in understanding and mitigating negative effects of SWBLI. The goal of this research is to demonstrate the effect of bleed holes on shock stability using the OVERFLOW CFD solver to inform the planning of an Air Force Research Laboratory (AFRL) SWBLI wind tunnel experiment. First, a two-dimensional, flat plate, single-hole configuration was developed. Massflow discrepancies of 14.8% were initially observed but reduced to 0% by analyzing the internal flow interaction with the boundary condition. Shock unsteadiness is then characterized using a canonical forward-facing step over a flat plate, which showed peaks at 5.8, 12.1, 31.2, 44.5, and 54.9 hertz. Though the final step of simulating bleed on the baseline forward-facing step was not achieved, promising time and frequency domain analysis techniques were demonstrated.

AFIT Designator

AFIT-ENY-MS-18-M-247

DTIC Accession Number

AD1056556

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