Modeling of Variable Surface Roughness Effects in Turbulence Models for Rotorcraft Applications

Award Information
Agency: Department of Defense
Branch: Army
Contract: Ww911W6-14-G0003
Agency Tracking Number: A2-5408
Amount: $468,957.00
Phase: Phase II
Program: SBIR
Awards Year: 2014
Solicitation Year: 2012
Solicitation Topic Code: A12-075
Solicitation Number: 2012.2
Small Business Information
22941 Mill Creek Drive, Laguna Hills, CA, 92653-1215
DUNS: 188465819
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: Y
Principal Investigator
 Jacob George
 Sr. Scientist
 (949) 553-0688
 jageorge@metrolaserinc.com
Business Contact
 Cecil Hess
Title: President
Phone: (949) 553-0688
Email: cecilh@metrolaserinc.com
Research Institution
N/A
Abstract
The goal of this Phase II program is to develop a simulation tool to estimate the aerodynamic effects of variable surface roughness, such as from the surface abrasion of helicopter rotor blades and the protective coatings that are applied to counteract it. The modeling is based on a displacement of origin methodology, within the k-omega turbulence model frameworks. Our initial investigations suggest that this method is effective in non-equilibrium boundary layers. Additionally we will implement and develop intermittency based transition models. We will work with OpenFoam and OVERFLOW CFD solvers which are widely used in the rotorcraft, and aerodynamics community. We expect to develop a state-of-the-art simulation tool for rotor blade drag estimation, and demonstrate capabilities through rotor simulations. The work plan consists of implementation and extension of the roughness models, in addition to development of a general capability for user defined measures of surface roughness. The effort includes verification and validation and also includes experiments to develop validation for configurations that are relevant to the rotorcraft application roughness strips and representative pressure gradients. A transition model will be implemented, with verification and validation using available transition data on turbine geometries.

* Information listed above is at the time of submission. *

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