Unsteady Airfoil Design Optimization with Application to Dynamic Stall

Award Information
Agency:
Department of Defense
Amount:
$99,986.00
Program:
SBIR
Contract:
W911W6-11-C-0036
Solitcitation Year:
2011
Solicitation Number:
2011.1
Branch:
Army
Award Year:
2011
Phase:
Phase I
Agency Tracking Number:
A111-002-0286
Solicitation Topic Code:
A11-002
Small Business Information
Combustion Research and Flow Technology, Inc.
6210 Kellers Church Road, Pipersville, PA, -
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
929950012
Principal Investigator
 Vineet Ahuja
 Senior Research Scientist
 (215) 766-1520
 vineet@craft-tech.com
Business Contact
 Brian York
Title: Treasurer and Principal Scientist
Phone: (215) 766-1520
Email: york@craft-tech.com
Research Institution
 Stub
Abstract
One of the persistent problems affecting the aerodynamic performance of rotorcrafts is retreating blade stall that results in large pitching moments and hazardous control situations. Our primary goal is the development of an unsteady design optimization framework that can be applied to refine rotorcraft blade designs by delaying the onset of stall, and improving aerodynamic performance as well as lift cycle hysteresis. The proposed unsteady optimization framework utilizes an evolutionary algorithm, automated shape parameterization tool and a novel CFD derived analysis methodology for evaluating the objective function. The novel part of the framework is the unsteady analysis procedure that combines CFD, a modified Proper Orthogonal Decomposition Procedure (POD) and an Artificial Neural Network (ANN) to evaluate the objective function with the accuracy of a time-spectral method but at a fraction of the cost. The framework is readily applicable to Multi-Disciplinary Optimization (MDO) thereby leading to the inclusion of aero-elastic and aero-acoustic effects with minimal development. In Phase I we will demonstrate the applicability of the proposed framework to the shape optimization of a pitching airfoil without stall. In Phase II the problem of shape optimization with dynamic stall on a three-dimensional rotorcraft blade with and without MDO will be attempted.

* information listed above is at the time of submission.

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