Optical Mach Probe

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX12CD70P
Agency Tracking Number: 115152
Amount: $124,987.00
Phase: Phase I
Program: SBIR
Awards Year: 2012
Solitcitation Year: 2011
Solitcitation Topic Code: A4.01
Solitcitation Number: N/A
Small Business Information
Michigan Aerospace Corporation
1777 Highland Drive, Suite B, Ann Arbor, MI, -
Duns: 969868298
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Daniel Bivolaru
 Principal Investigator
 (734) 975-8777
 dbivolaru@michiganaerospace.com
Business Contact
 John Dodds
Title: Business Official
Phone: (734) 975-8777
Email: jdodds@michaero.com
Research Institution
 Stub
Abstract
Michigan Aerospace Corporation (MAC) proposes to advance NASA's nonintrusive spatially- and temporally-resolved Interferometric Rayleigh Scattering (IRS) technology to perform additional multiple properties measurements in high-speed flows. In particular, an instantaneous nonintrusive Optical Mach Probe (OMP) to obtain the Mach number and the flow angularity among the flow density, translational temperature, and the bulk velocity is proposed. Other turbulence-specific parameters, such as components of the stress and heat flux tensors, the mean and fluctuations of properties are obtained from these measurements.During Phase I of this effort, the optical, mechanical, electrical, and software engineering models of the instrument will be developed for the specific application. The prototype development and preliminary tests to demonstrate the technique could be performed in Phase II at NASA through the adaptation of NASA's existing technologies.This proposal is in response to the NASA SBIR Phase I, Topic: A4 Aeronautics Test Technologies, Subtopic: A4.01 Ground Test Techniques and Measurement Technology. The objective is to develop and demonstrate nonintrusive measurement technologies to increase techniques' capabilities and characterize ground test facility flow performance in terms of flow quality, turbulence intensity, and Mach number measured up to and including hypersonic speed regimes.

* information listed above is at the time of submission.

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