Diagnostic Techniques for High Speed Flows

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-06-C-3602
Agency Tracking Number: F051-242-0509
Amount: $210,000.00
Phase: Phase II
Program: SBIR
Awards Year: 2006
Solicitation Year: 2005
Solicitation Topic Code: AF05-242
Solicitation Number: 2005.1
Small Business Information
2766 Indian Ripple Rd, Dayton, OH, 45440
DUNS: 884812025
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Sivaram Gogineni
 Vice President
 (937) 255-8446
Business Contact
 Larry Goss
Title: President
Phone: (937) 429-4980
Email: gosslp@innssi.com
Research Institution
The U.S. Air Force Research Laboratory has determined that a need exists for new diagnostic instrumentation capable of obtaining quantitative flow data in large scale aerodynamic facilities without reliance on molecular or particle seeding. This Phase II Small Business Innovative Research proposal offers a new avenue for non-intrusive instrumentation based upon the application of ultra-fast laser technology to a class of optical diagnostic known as Flow Tagging Velocimetry, with particular emphasis on the high subsonic (Mach ~0.7) to moderate supersonic (Mach ~2-3) flow regimes. In Phase I experiments were successfully performed demonstrating all critical elements associated with our proposed enhancements to the oxygen-based flow tagging method known as RELIEF (Raman Excitation + Laser Induced Electronic Fluorescence). Phase II, building upon the results of Phase I, will focus on optimization of the optical technologies demonstrated in Phase I and delivery and integration of a complete ultra-fast flow tagging system to the AFRL Air Vehicles Directorate Trisonic Flow Facility. The instrumentation will be modular in design and will also be readily adaptable to other optical diagnostic methods, most notably Planar Imaging Velocimetry (PIV). The Phase II program will culminate in a sequence of velocity field measurements of the flow produced external to and within a transonic cavity model.

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

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