An Experimental/Computational Investigation of the Response of a Compliant Panel to Turbulent and Transitional Shock Wave/Boundary Layer Interactions in Hypersonic Flow
Abstract
Experiments at Mach 6 and 10 on a flat-plate/ramp configuration with an embedded compliant panel are conducted to investigate the fluid-thermal-structural interaction (FTSI) induced by a nominally two-dimensional shockwave/ boundary-layer interaction (SWBLI) for various ramp angles and panel back pressures. Stereo photogrammetry, focusing schlieren, surface pressure measurements, and IR thermography are used to characterize the panel mechanical and thermal state as well as the unsteady flowfield characteristics. Corresponding simulations of the Mach 6 flow approaching and interacting with a 35 degree ramp to develop a fundamental understanding of the fluid-ramp interaction. Finally, an unsteady aerodynamic model is developed that improves the quantitative accuracy of fluid-thermal-structural interaction predictions at conditions for which piston theory is known to be in error.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 16, 2022
- Accession Number
- AD1190047
Entities
People
- Laurence Stuart
Organizations
- University of Maryland