Development of Adaptive Vorticity Confinement Based CFD Methodology for Rotorcraft Applications

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$79,996.00
Award Year:
2014
Program:
SBIR
Phase:
Phase I
Contract:
N68335-14-C-0029
Award Id:
n/a
Agency Tracking Number:
N132-092-0823
Solicitation Year:
2013
Solicitation Topic Code:
N132-092
Solicitation Number:
2013.2
Small Business Information
60 Hazelwood Drive, P. O. Box 3001, Champaign, IL, 61826-
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
792045713
Principal Investigator:
BonoWasistho
CFD Group Lead
(256) 542-8123
bwa@illinoisrocstar.com
Business Contact:
WilliamDick
President & CEO
(217) 417-0885
wdick@illinoisrocstar.com
Research Institute:
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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