Unsteady Airfoil Design Optimization with Application to Dynamic Stall

Award Information
Agency: Department of Defense
Branch: Army
Contract: W911W6-11-C-0036
Agency Tracking Number: A111-002-0286
Amount: $99,986.00
Phase: Phase I
Program: SBIR
Awards Year: 2011
Solicitation Year: 2011
Solicitation Topic Code: A11-002
Solicitation Number: 2011.1
Small Business Information
6210 Kellers Church Road, Pipersville, PA, -
DUNS: 929950012
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Vineet Ahuja
 Senior Research Scientist
 (215) 766-1520
Business Contact
 Brian York
Title: Treasurer and Principal Scientist
Phone: (215) 766-1520
Email: york@craft-tech.com
Research Institution
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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