Variable-Fidelity Wake Prediction Methods for Improving CFD

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-09-C-0335
Agency Tracking Number: N09A-009-0562
Amount: $69,969.00
Phase: Phase I
Program: STTR
Awards Year: 2009
Solicitation Year: 2009
Solicitation Topic Code: N09-T009
Solicitation Number: 2009.A
Small Business Information
34 Lexington Avenue, Ewing, NJ, 08618
DUNS: 096857313
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 GLEN R WHITEHOUSE
 ASSOCIATE
 (609) 538-0444
 GLEN@CONTINUUM-DYNAMICS.COM
Business Contact
 Barbara Agans
Title: DIRECTOR, BUSINESS ADMINISTRATION
Phone: (609) 538-0444
Email: BARBARA@CONTINUUM-DYNAMICS.COM
Research Institution
 GEORGIA INSTITUTE OF TECHNOLOGY
 R P Hart
 505 TENTH STREET NW
ATLANTA, GA, 30332
 (404) 894-6929
 Nonprofit college or university
Abstract
Accurate performance prediction is essential for developing rotorcraft and supporting flight operations. Current grid-based CFD can, in principle, model the complete rotorcraft, but is hampered by excessive numerical dissipation of vorticity. Thus, common methods fail to predict adequately the unsteady rotor and fuselage loading. Moreover, the critical dynamic interface (DI) problem of a rotorcraft approaching and landing on a ship cannot be predicted fully with current methods. Continuum Dynamics, Inc. (CDI) and Georgia Institute of Technology (GT) propose to directly address these limitations while simultaneously supporting naval operations by developing a suite of variable-fidelity wake prediction methods for improving CFD and enabling breakthrough DI simulation capabilities. This approach builds upon work at CDI and GT in CFD, free-wakes and hybrid analyses to directly address issues of improving rotorcraft CFD accuracy, reducing turn-around time by coupling CFD to CDI’s CHARM and VorTran-M wake solvers. Moreover, given the inherent capabilities of the proposed tools, performing fully-interacting fully-coupled DI simulations will become viable for the first time! Phase I will see the preliminary integration of the flow solvers and proof-of-concept calculations will be performed. Phase II would see formal validation, demonstration, and commercialization of these approaches for accelerating and improving rotorcraft CFD.

* Information listed above is at the time of submission. *

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