Dynamic Hybrid RANS/LES Modeling of Interior Nozzle Flows and Jet Plumes

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-14-C-0048
Agency Tracking Number: N132-102-0843
Amount: $79,957.00
Phase: Phase I
Program: SBIR
Awards Year: 2014
Solicitation Year: 2013
Solicitation Topic Code: N132-102
Solicitation Number: 2013.2
Small Business Information
ATA Engineering, Inc
13290 EVENING CREEK DRIVE SOUTH, Suite 250, San Diego, CA, 92128
DUNS: 133709001
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Parthiv Shah
 Senior Project Engineer
 (858) 480-2101
 parthiv.shah@ata-e.com
Business Contact
 Ronan Cunningham
Title: Director, Business Develo
Phone: (858) 429-9835
Email: ronan.cunningham@ata-e.com
Research Institution
N/A
Abstract
ATA Engineering proposes to simulate complex interior and exterior flowfields of hot, supersonic aircraft engine nozzles by applying a novel dynamic hybrid RANS/LES (DHRL) modeling framework coupled to the Loci/CHEM (CHEM) finite-volume flow solver. DHRL is code- and turbulence model-independent. It dynamically determines the appropriate interface between large eddy simulation (LES) and Reynolds Averaged Navier-Stokes (RANS) portions of a computational domain, ensuring smooth and continuous turbulence production across the interface. It has been validated on attached and separated flows ranging from transitional cardiovascular devices to very high Reynolds number ship hydrodynamics. CHEM is a massively parallelizable solver for highly compressible flows both with/without real gas properties and chemistry. The technical approach will first demonstrate and validate that DHRL provides LES accuracy at hybrid RANS/LES costs on a test problem relevant to high-performance engine nozzles. Best practices for grid generation, time stepping, and turbulence model selection will then be applied to full nozzle simulations on a government-furnished geometry. Finally, a technical plan will be outlined for inclusion of real geometry effects including throttle transients, advanced wall boundary conditions, and realistic inflow turbulence.

* information listed above is at the time of submission.

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