An experimental/computational investigation of the response of a compliant panel to turbulent and transitional shock-wave/boundary-layer interactions in hypersonic flow
Abstract
We propose a combined experimental/numerical study of the fluid-structure interaction (FSI) induced by a flexible panel exposed to a two-dimensional hypersonic shock-wave/boundary-layer interaction (SWBLI), under both turbulent and transitional upstream boundary-layer conditions. The proposed investigation will take advantage of hypersonic facilities at NASA Langley through an agreement with UMD, and a state-of-the-art computational infrastructure at the University of Illinois, Urbana-Champaign (UIUC). Experiments will be performed on a flat-plate/ramp configuration to produce a planar SWBLI, with both transitional and fully turbulent incoming boundary layers (achieved by varying the unit Reynolds number), with the compliant panel located downstream of the plate-ramp junction. The ramp angle will be varied to produce a range of interaction strengths at both Mach 6 (Langley 20” Mach-6tunnel) and Mach 10 (Langley 31” Mach-10 tunnel). Various measurement techniques will be implemented, including fast-response pressure transducers, high-speed Schlieren and IR thermography, and marker-tracking photogrammetry for panel deformation measurements. Measurements of the turbulent SWBLI/FSI will be compared with results from high-fidelity coupled fluid-structure simulations, accurately representing experimental conditions, which will provide a detailed picture of the interaction dynamics. Finally, a global mode-based analysis will be performed to provide a physics-based reduced-order model of the coupled fluid-structure system.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 21, 2022
- Source ID
- FA95502110249XX0
Entities
People
- Stuart Laurence
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Maryland