Combined Viscous Vortex Particle Method with a Near Body CFD Solver for Rotorcraft Comprehensive Analysis

Award Information
Agency:
Department of Defense
Branch
Army
Amount:
$70,000.00
Award Year:
2009
Program:
SBIR
Phase:
Phase I
Contract:
W911W6-10-C-0017
Award Id:
92116
Agency Tracking Number:
A092-020-0191
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
1330 Charleston Road, Mountain View, CA, 94043
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
149732315
Principal Investigator:
Chengjian He
Vice President of Research
(650) 968-1464
he@flightlab.com
Business Contact:
Donna Carrig
Vice President of Finance
(650) 968-1464
donna@flightlab.com
Research Institution:
n/a
Abstract
The unsteady rotorcraft wake emanated from rotors, wings, and lifting surfaces is a physically complicated problem and remains a difficult aspect of comprehensive rotorcraft analysis. The recent development of a viscous vortex particle method (VVPM) shows very high promise for providing a first-principle-based solution to the unsteady wake problem. Applying VVPM for wake vorticity transportation, while using a modern near body CFD solver for resolving vorticity sources of the rotor blades, fuselage, and lifting surfaces (such as wing and stabilators), will provide an efficient hybrid rotorcraft aerodynamic solution in support of comprehensive rotorcraft modeling and analysis. This SBIR will develop a formulation of the coupled VVPM/CFD/CSD interface and associated algorithms for numerical simulation. The coupled solution will be demonstrated through test problems for prediction of rotor wake vorticity variation and rotor airloads and response. The proposed SBIR research emphasizes the fundamental rotorcraft wake dynamics modeling and resulting airloads prediction accuracy. The research and development will also emphasize the integration of the state-of-the-art VVPM with a modern rotorcraft comprehensive analysis program, such as RCAS, in support of rotorcraft research, design, and engineering applications.

* information listed above is at the time of submission.

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