Rapid Computational Fluid Dynamics (CFD) Methodology for Rotorcraft Maneuver Analysis

Award Information
Agency: Department of Defense
Branch: Army
Contract: W911W6-08-C-0051
Agency Tracking Number: A062-009-0222
Amount: $729,776.00
Phase: Phase II
Program: SBIR
Awards Year: 2008
Solicitation Year: 2006
Solicitation Topic Code: A06-009
Solicitation Number: 2006.2
Small Business Information
3146, Greenwood road, Ames, IA, 50014
DUNS: 877929125
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Andrew Hollingsworth
 Engineer
 (515) 292-9646
 nappi@sukra-helitek.com
Business Contact
 R Nappinnai
Title: President
Phone: (515) 292-9646
Email: Nappi@sukra-helitek.com
Research Institution
N/A
Abstract
The lack of proper estimation of air loads encountered during transient maneuvers introduces excessive design conservatism. A reduced fidelity CFD methodology based on momentum source (Rot3DC) and a comprehensive analysis code (RCAS) were coupled in Phase I to validate the ``proof-of-concept'' that such system is capable of rapidly analyzing steady and transient maneuvers. The tightly coupled system for an isolated rotor was shown to converge wherein the inflow was supplied by Rot3DC and the trim state was obtained from RCAS. In Phase II, the ``proof-of-concept'' will be extended to complete configurations with multiple rotors and fuselage. In addition to the kinematics of the rotor (trim) the structural deformations of the rotor blades will be fully included in the Phase II system. The rotor model in coupled Phase I analysis was restricted to translating discs. In Phase II, the momentum source model will be extended to unsteady rotors where individual blades will be recognized. The tool will be tested using candidate vehicles provided by the Army. Enhancements such as parallelization and complete design of a user interface will be investigated for implementation in Phase III.

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

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