High-Speed High-Reynolds-Number Boundary Layer Measurements and Modeling
Abstract
Accurate modeling and simulation of hypersonic high-Reynolds-number turbulent flows isessential in the design of future Navy flightsystems. Modeling errors, up to 50%, are observed inthe simulation of the wall heat transfer for high-speed vehicles at Navy relevant condition. Ourhypothesis is that these errors stem from the ubiquitous use of empirical near-wall turbulenceformulations with limited calibration. The objective of this research is to reduce modelinguncertainty in the prediction of wall heat transfer to values consistent with those attainableexperimentally (~15%). Our approach consists of the following four goals: (1) Produce high-speedhigh-Reynolds-number data, including wall temperature and pressure gradient effects to informmodel development, calibration, and revision. (2) Produce non-intrusive velocity and temperatureboundary layer profile measurements. (3) Assess and advance industry standard and develop newreduced order transport-equation closure models. And (4), employ data assimilation methods toinform efficient model calibration and advancement. The proposed test parameters availablewithin the TAMU hypervelocity expansion tunnel (HXT) include high-speeds (M½ = 3#6), high-Reynolds-numbers (Ret = 1000#10,000), variable wall temperature ratios (Twall/Taw = 0.2#0.7),and pressure gradients [Clauser parameter =½(0.1#1.0)]. Three experimental campaigns areproposed to quantify Reynolds-number, wall temperature, and pressure gradient effects: (i) Planarwedges with for rapid parametric studies over Mach number, Reynolds number, wall temperatureratio, and entropy layer (varying nose bluntness). (ii) Ogive models to examine favorable pressuregradients, with high fidelity direct numerical simulation (DNS) to facilitate supervised machinelearning. And (iii), a hollow cylinder model with wall curvature drivencombined pressuregradients to characterize the rate of response of turbulence to inform model simplifications. Themeasurements willinclude wall heat transfer, skin friction, and profiles of velocity andtemperature. The MHz pulse burst lasers will be used for non-intrusive field data in the HXTfacility. The deliverables from this project include extensive data (experimental and numerical)closing a clear gap in the national database and a new suite of physics-based turbulence modelsfor the Reynolds stress and turbulent heat flux suitable for Navy relevant flows, which closes along-standing gap in the national modeling and simulation knowledgebase. We intend tocollaborate with Ohio State University, Johns Hopkins Applied Physics Lab, and Sandia NationalLabs for additional DNS studies and physical insight.Publicly Releasable
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Apr 12, 2023
- Source ID
- N000142312302
Entities
People
- Rodney D W Bowersox
Organizations
- Office of Naval Research
- Texas Engineering Experiment Station
- United States Navy