Accession Number:

AD1190047

Title:

An Experimental/Computational Investigation of the Response of a Compliant Panel to Turbulent and Transitional Shock Wave/Boundary Layer Interactions in Hypersonic Flow

Descriptive Note:

[Technical Report, Final Report]

Corporate Author:

UNIVERSITY OF MARYLAND, COLLEGE PARK

Personal Author(s):

• STUART, LAURENCE

Report Date:

2022-12-16

Pagination or Media Count:

11

Abstract:

Experiments at Mach 6 and 10 on a flat-plateramp 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-structuralinteraction predictions at conditions for which piston theory is known to be in error.

Descriptors:

• fluid dynamics
• computational fluid dynamics
• boundary layer
• computational science
• fluid mechanics
• reynolds number
• air force
• air force research laboratories
• back pressure
• physics laboratories
• shock waves
• universities
• aeroelasticity
• frequency
• hypersonic flow
• layers
• leading edges

Subject Categories:

Distribution Statement:

[A, Approved For Public Release]