MEASUREMENT AND MODELING OF AN OBLIQUE SHOCK GRAZING A COMPLIANT PANEL
Abstract
The unsteady, high-speed aerodynamic flows present in hypersonic flight systems generate large amplitude thermo-mechanical loads on the underlying structure, causing it to dynamically respond and modify the original flow field. This proposal will study the fluid-thermal-structural interaction (FTSI) that occurs when a fin-generated oblique shock from a Mach 6-10 flow grazes a flat metallic panel embedded within an otherwise rigid fixture. Experiments conducted in the University of Maryland high-temperature Ludwieg tube will use focused schlieren, photogrammetry, and pressure and temperature sensitive paints to measure the unsteady aerodynamics and the dynamic panel response over a range of Mach numbers, Reynolds numbers, and panel thicknesses. A fiber-optic technique will also be developed to measure the panel dynamic thermo-mechanical response. High-fidelity FTSI simulations will be performed of the shock-boundary layer-panel interaction at a subset of the experimental conditions to complement measurements with detailed space-time predictions as well as to provide data to inform a new unsteady aerodynamic model for use in a FTSI reduced-order model suitable for estimating the flutter and forced response of panels subjected shock-generated loads.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 07, 2023
- Source ID
- FA95502210246
Entities
People
- Daniel J. Bodony
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Illinois Urbana–Champaign