Date of Award
3-10-2010
Document Type
Thesis
Degree Name
Master of Science in Aeronautical Engineering
Department
Department of Aeronautics and Astronautics
First Advisor
Paul I. King, PhD
Abstract
The isolator of the scramjet decelerates the incoming high Mach flow to a lower Mach number and stabilizes the flow before it enters the combustor. Because of the unsteady combustion phenomenon and inconsistent completeness of the combustion, pressures within the combustor can vary drastically. These pressure variations can propagate forward and affect the flow field in the isolator - worst case unstarting the inlet. In this research, the shock train location versus the back-pressure is examined experimentally. The back-pressure is artificially created by symmetric (top & bottom) ramps that can close the flow area. Raising/lowering ramps result in higher/lower back-pressure. Higher back-pressure moves the shock train forward, with too high a back-pressure causing un-start. This experiment is conducted for a variation in Reynolds number, ramp angle, and two incoming Mach #s, and will result in a relationship between back-pressure and shock train location for various airflow conditions.
AFIT Designator
AFIT-GAE-ENY-10-M17
DTIC Accession Number
ADA517638
Recommended Citation
Paek, Richard I., "Back-pressure Effect on Shock-Train Location in a Scramjet Engine Isolator" (2010). Theses and Dissertations. 2048.
https://scholar.afit.edu/etd/2048