An experimental investigation of the two-stream, supersonic, near wake flowfield behind a finite-thickness base

The interaction region generated by separation of two supersonic streams past a finite-thickness base occurs in high-speed flight and characterizes the aft-end flowfield of powered missiles in supersonic flight. In order to examine fundamental mechanisms and interactions ongoing in this near-wake region, an experimental investigation was conducted to obtain mean and turbulence data in a wind tunnel. The test section produced a Mach 2.56 upper stream and a Mach 2.05 lower stream which both undergo geometric separation past a finite-thickness plate and experience strong expansion and mixing processes before eventual recompression, reattachment, and redevelopment of the wake flow. This near-wake flowfield is characterized by strong velocity and density gradients, viscous interactions, high turbulence levels, and energetic recirculation. The data was obtained using Schlieren photographs, stagnation and static pressure measurements, and laser Doppler velocimeter (LDV) measurements. The primary tool was a two-color, two-component LDV system. The data was analyzed in component approach consistent with the Chapman-Korst model.

Name thesis:degree_name

Ph.D.

Level thesis:degree_level

Dissertation

Discipline thesis:degree_discipline

Mechanical Engineering

Grantor

University of Illinois at Urbana-Champaign

Year dc:date

2011

Author dc:creator

• Amatucci, Vincent Andrew

Contributors dc:contributor

• Addy, A.L.
• Dutton, J. Craig

• Engineering, General
• Engineering, Aerospace
• Engineering, Mechanical

Statement dc:rights

• Copyright 1990 Vincent Andrew Amatucci

Language dc:language

eng

Identifier

AAI9026120
(UMI)AAI9026120

OAI identifier oai:identifier

oai:www.ideals.illinois.edu:2142/20306