Reynolds-Averaged Modeling and Real-Gas Effects in Hypersonic Turbulent Boundary Layers
Abstract
Concerns regarding the competitiveness of our national defense resources are steadily on the rise as non-allied countries overseas continue to strengthen their capabilities in hypersonic penetrating weapons. The current proposal aims at training the next generation of personnel in computational prediction methods for hypersonic flows, strengthening the Department of Defense readiness for the development of hypersonic vehicles.The currently existing large errors between predicted and measured turbulent aerodynamic heating and drag warrant the urgent development of multi-fidelity models to improve the accuracy models used by DoD computational scientists. In particular, heating rates due to fully turbulent hypersonic boundary layers significantly challenge structural integrity of high-speed vehicles and reduce the available payload. Fundamental understanding of the flow structure inthis regime will enable improved prediction and hence more effective vehicle design from an aerodynamic and materials perspective.The overall objectives of the BASE PERIOD are to enhance the fundamental knowledge of nearwall hypersonic turbulence to inform both Large-Eddy Simulation (LES) and Reynolds-Averaged Navier-Stokes (RANS) modeling of hydrodynamic and thermal Reynolds stresses; Specifically, Task I will target flow conditions that hypervelocity projectiles (HVP) operate with Wall Modeled LES (WMLES). This includes Mach numbers of about 3-6 and sea-levelconditions of Reynolds Numbers of 10-100 million. The common ogive shape of a HVP generated strong favorable pressure gradient conditions (FPG), but test cases at zero (ZPG) and adverse (APG) conditions will be considered.Task II will look at higher altitude flight (Re = 1-10 million focusing on real-gas effects and chemical reactions in fully turbulent conditions. This last class of high enthalpy flows falls in the domain of other agencies as well (AFOSR, NASA, etc.), enhancing synergistic cooperation with the Navy. The angle to Task II is the prediction of oxidation rates of thermal protection shields, such as carbon/carbon ceramics, and their survivability. As such, it is at the cross-roads between aerodynamics and materials sciences. The dataset generated will be direct numerical simulations of real-gas effects in high-speed boundary layers matching recently published linear stability results by Wartemann et al. AIAA 2018.The long-term objective (Task III, OPTION PERIOD) is to assist in the development of hypersonic capabilities in AV-CREATE s Navier-Stokes solver, Kestrel -- already being used in Dr. Scalo s group. The proposed effort relies on the creation of dataset will also include data from Kestrel simulations to obtain the steady laminar flow over Hypervelocity Projectiles (HVP), highly-resolved transitional and fully turbulent boundary layers with adverse pressuregradient effects (APG). If funded, the present proposal will prompt the formation of a new NATO AVT-240 Task force focused on the characterization of fully developed near-wall hypersonic turbulence. The task force will be aimed at the creation of an international team with collaborators from the UK, Germany, France and Belgium; possibly in coordination with (but separate from) the currently existing AVT-240 NATO task force.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jun 17, 2020
- Source ID
- N000142012662
Entities
People
- Carlo Scalo
Organizations
- Office of Naval Research
- United States Navy
- University of Virginia