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

Award Information
Agency:
Department of Defense
Branch
n/a
Amount:
$729,987.00
Award Year:
2010
Program:
SBIR
Phase:
Phase II
Contract:
W911W6-10-C-0058
Award Id:
92116
Agency Tracking Number:
A2-4188
Solicitation Year:
2009
Solicitation Topic Code:
A09-020
Solicitation Number:
2009.2
Small Business Information
635 Vaqueros Avenue, Sunnyvale, CA, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
149732315
Principal Investigator:
Chengjian He
Vice President of Researc
(408) 523-5100
he@flightlab.com
Business Contact:
Donna Carrig
Vice President of Finance
(408) 523-5100
donna@flightlab.com
Research Institute:
n/a
Abstract
The unsteady rotor wake is a complicated flow problem and remains a challenging aspect of comprehensive rotorcraft analysis. The Phase I research has shown that a viscous vortex particle method (VVPM) can provide a first-principle-based solution to the challenging rotor wake problem. Applying VVPM for wake vorticity transportation, while using a modern near body CFD solver for resolving vorticity sources of the rotor blades or fuselage will render an effective hybrid aerodynamic solution in support of comprehensive rotorcraft analysis. This Phase II SBIR will fully develop and implement the coupled VVPM/CFD/CSD solution for an accurate prediction of the rotor wake vorticity variation and the rotor airloads calculation. The proposed SBIR research emphasizes the fundamental rotorcraft wake dynamics modeling and resulting airloads prediction accuracy. The development will address 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. The Phase II work will also emphasize the modularization of VVPM to make it sufficiently versatile that it can be used as a plug-in module for general solver integration platforms, such as HI-ARMS.

* information listed above is at the time of submission.

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