Fast Lifting Surface Models for Rotorcraft Analysis

Award Information
Agency: Department of Defense
Branch: Army
Contract: W911W6-12-C-0013
Agency Tracking Number: A2-4838
Amount: $729,980.00
Phase: Phase II
Program: SBIR
Awards Year: 2012
Solicitation Year: 2010
Solicitation Topic Code: A10-148
Solicitation Number: 2010.3
Small Business Information
Continuum Dynamics, Inc.
34 Lexington Avenue, Ewing, NJ, -
DUNS: 096857313
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Daniel Wachspress
 Senior Associate
 (609) 538-0444
Business Contact
 Barbara Agans
Title: Director, Business Admini
Phone: (609) 538-0444
Research Institution
Current comprehensive rotorcraft analyses typically use lifting line theories coupled with 2D look-up tables to determine rotor blade lift, drag and pitching moment. These methods cannot directly capture 3D flow effects that influence the aerodynamic characteristics of advanced planforms, complex tip-shapes and low aspect ratio wing/tail surfaces. CFD codes have been coupled to comprehensive codes to provide this capability, but these coupled solutions are too computationally expensive for daily design work. The Phase I effort demonstrated the potential of lifting surface blade models to partially bridge the gap between lifting line models and full CFD solutions without excessive increase in computation time. The lifting surface model developed in Phase I was shown to better predict lift, drag and pitching moment than lifting line models near the tip of the blade and where strong blade-vortex interactions occurred. The proposed Phase II effort would further enhance and accelerate this lifting surface blade model and then provide comprehensive documentation of its effectiveness in modeling fixed and rotating wings in both steady and unsteady flow. The new lifting surface blade model would then be implemented, demonstrated and delivered as a new option within the U.S. Army"s Rotorcraft Comprehensive Analysis System (RCAS).

* information listed above is at the time of submission.

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