Development of Adaptive Vorticity Confinement Based CFD Methodology for Rotorcraft Applications

Award Information
Agency:
Department of Defense
Amount:
$79,996.00
Program:
SBIR
Contract:
N68335-14-C-0029
Solitcitation Year:
2013
Solicitation Number:
2013.2
Branch:
Navy
Award Year:
2014
Phase:
Phase I
Agency Tracking Number:
N132-092-0823
Solicitation Topic Code:
N132-092
Small Business Information
IllinoisRocstar LLC
60 Hazelwood Drive, P. O. Box 3001, Champaign, IL, 61826-
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
792045713
Principal Investigator
 Bono Wasistho
 CFD Group Lead
 (256) 542-8123
 bwa@illinoisrocstar.com
Business Contact
 William Dick
Title: President & CEO
Phone: (217) 417-0885
Email: wdick@illinoisrocstar.com
Research Institution
N/A
Abstract
The accurate representation of the rotor wake, especially the tip vortex structure, in a computationally efficient and algorithmically straight forward way is crucial for prediction of rotor aerodynamic performance, noise emission, and rotor structural dynamics. A promising approach for design and optimization is the vorticity confinement (VC) method that minimizes the numerical diffusion of vorticity in the vortical flow regions. The remaining challenge is to remove the tuning of model parameters to make the method truly predictive and robust. We will develop a fully adaptive VC (AVC) method based on a new formulation. Auxiliary numerical treatments will be implemented that can detect and mitigate potential instabilities, borrowing the idea from shock capturing schemes. We will assess the AVC method in different types of numerical schemes, particularly the spatial discretization scheme. A procedure to determine model parameters dynamically will be constructed dependent on the numerical schemes employed. As a result, it is expected that the new VC methodology will be broadly applicable and characterized for a range of numerical schemes. The Phase II AVC implementation will address rotorcraft applications, including strong transients, rotor noise due to blade vortex interaction, rotor-body nonlinear interactions, and aeroelasticity of the rotor blades.

* information listed above is at the time of submission.

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