Coupled Viscous Vortex Particle Method and Unstructured CFD Solver for Rotorcraft Aerodynamic Interaction Modeling

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-10-C-0382
Agency Tracking Number: N09A-009-0132
Amount: $749,997.00
Phase: Phase II
Program: STTR
Awards Year: 2010
Solicitation Year: 2009
Solicitation Topic Code: N09-T009
Solicitation Number: 2009.A
Small Business Information
Advanced Rotorcraft Technology, Inc.
635 Vaqueros Avenue, Sunnyvale, CA, -
DUNS: 149732315
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Chengjian He
 Vice President of Researc
 (408) 523-5100
 he@flightlab.com
Business Contact
 Donna Carrig
Title: Vice President of Finance
Phone: (408) 523-5123
Email: donna@flightlab.com
Research Institution
 Rensselaer Polytechnic Institute
 Angela Stark
 Research Adminstration
110 8th Street
Troy, NY 12180, NY, 12180-
 (518) 276-6169
 Nonprofit college or university
Abstract
The rotorcraft aerodynamic interaction is a complicated problem and remains an extremely challenging aspect of rotorcraft analysis. This STTR is dedicated to developing a solution for the complicated rotorcraft aerodynamic interaction problem. The Phase I research coupled a state-of-the-art vortex particle method (VPM) with an unstructured Navier-Stokes CFD body surface solver and prototyped a hybrid solver for the complicated rotor/fuselage interaction problem. The hybrid solver successfully demonstrated an accurate solution for the prediction of the unsteady flow field of the rotor wake and the unsteady pressure over the fuselage surface due to the interacting rotor wake effect. Phase II will aim at a full development of the methodology and emphasize the application of the advanced hybrid tool for solving the complicated rotorcraft aerodynamic interaction problems. Phase II will further enhance the methodology, develop a standard flow solver coupling utility, and fully implement the hybrid methodology. Phase II will also evaluate the hybrid solution and compare the results with wind tunnel and flight test measurements to substantiate the hybrid modeling and analysis tool.

* information listed above is at the time of submission.

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