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Characterization of the Aero-Structure Environment of a Transonic Scaled Fighter (CASE-TSF)

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9550-13-C-0032
Agency Tracking Number: F12B-T12-0016
Amount: $149,912.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: AF12-BT12
Solicitation Number: 2012.B
Solicitation Year: 2012
Award Year: 2013
Award Start Date (Proposal Award Date): 2013-05-01
Award End Date (Contract End Date): 2014-02-01
Small Business Information
2780 Skypark Drive Suite 400
Torrance, CA -
United States
DUNS: 106823607
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Dana Howard
 Principal Investigator
 (310) 626-8652
Business Contact
 Zoltan Feher
Title: Manager, Contracts and Pricing
Phone: (310) 626-8384
Research Institution
 Virginia Tech
 Linda Bucy
1880 Pratt Drive, Suite 2006
Blacksburg, VA 24060, VA 24060-
United States

 (540) 231-5281
 Federally Funded R&D Center (FFRDC)

ABSTRACT: NextGen Aeronautics Inc. proposes use of rapid prototyping (RP) technologies, design process improvements, and novel sensing technologies to significantly reduce time and cost of transonic aeroelastic wind tunnel model development and improve their direct correlation to CFD data. The use of modern RP technologies will allow for model design variations such as variable modulus (stiffness) structures, variable surface qualities, direct structural integration, and rapid configuration / OML changes while reducing cost and time by reducing material waste, machine time, and part reduction. Development of a design pipeline leveraging these techniques will further reduce the effort of producing families of models with a range of variable parameters (OML, stores, planform, structural characteristics, etc). Lastly, by incorporating novel sensor technologies both within the model structure and within the tunnel system, correlation of tunnel test data to CFD predictions can be significantly improved. The team will review multiple RP techniques, sensor options, and develop a nominal design pipeline to allow for optimal model development. The final processes and sensors will be utilized to develop a family of models for evaluation and eventual construction. BENEFIT: Currently large aerospace companies and organizations conduct transonic aeroelastic wind tunnel model testing to validate in-house developed engineering tools and FEA/CFD codes. Unfortunately, the tools and data created from these efforts are largely unavailable to the public and academia and the cost of testing remains significantly high for smaller organizations to reproduce. Improvements in fabrication and design of parametrically variable wind tunnel models would allow reduced cost and time in the development and testing of these models, thus putting such testing within their reach. In addition to reducing cost of model design and production, generation of suitable transonic aeroelastic wind tunnel test data within the public domain will directly benefit commercial and academic developers attempting to improve their CFD and CSE tools.

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

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