Turbulence Quantities in Supersonic and Hypersonic Flows

Project: Research project

Project Details

Description

Technical Proposal: Turbulence Quantities in Supersonic and Hypersonic FlowsPrincipal Investigator: Nick ParzialeThe overall objective of this proposal is to make high-quality measurements of turbulence quantities in supersonic and hypersonic flows for the purpose of fundamental physical understanding and code validation. We propose to test canonical geometries that include a hollow-cylinder flare (HCF) and a flat plate to be placed at variable angle-of-attack (AOA) to generate different US-Navy-relevant conditions in thewell-characterized Mach 6 Stevens Shock Tunnel. Pressure, heat-transfer, and skin-friction surface data will be collected in concert with tagging velocity (TV) which will serve as a comprehensive reference for high-speed turbulence computations. We will use high-speed Acetone Tagging Velocimetry (ATV) and Krypton Tagging Velocimetry (KTV) to acquire mean and fluctuating velocity profiles in previously inaccessible flows; the surface measurements will be made with well-characterized, commercially available sensors. The TV data will be analyzed to assess current scaling laws for high-speed turbulent boundary layers with a cold wall. Additionally, we will elucidate the structure via modal analysis (potentially proper orthogonal decomposition (POD)) and identify the effect of the flowstructure on downstream surface-mounted sensors and, in the case of the HCF, shock-wave/boundary-layer interactions. The impact of this work will be the physics-based assessment of reduced-order turbulence models, such as Reynolds-averaged Navier-Stokes (RANS) approach, with a mixture of surface and off-surface measurements at well-characterized conditions. Our research objectives are:Scientific Objective: Study the effects of Mach number, Reynolds number, wall-temperature-ratio, and geometry (HCF, plate) on turbulence scaling, statistics, and structure (Me = 3.5-6, Re_tau=rho_w u_tau delta mu_w = 400-7000, T_w/T_r = 0.18-0.7).Technical Objectives: Design and fabricate flat-plate model, and perform flow assessment at Mach 3.5-6.0 for operation at flight/cold enthalpy. Design, fabricate, and calibrate dedicated Mach 3.5 nozzle.Approved for Public Release.

StatusActive
Effective start/end date1/05/23 → …

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