Hydroxyl Tagging Velocimetry for Rocket Plumes

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$599,978.00
Award Year:
2009
Program:
STTR
Phase:
Phase II
Contract:
NNX09CB74C
Award Id:
87896
Agency Tracking Number:
070025
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
8 Chrysler, Irvine, CA, 92618
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
188465819
Principal Investigator:
Thomas Jenkins
Principal Investigator
(949) 949-0688
tjenkins@metrolaserinc.com
Business Contact:
Christina Arnold
Director of Administration
(949) 949-0688
Research Institution:
Vanderbilt University

2301 Vanderbilt Place
Nashville, TN, 37235 7749
(615) 322-3979
Nonprofit college or university
Abstract
A non-intrusive method for measuring velocities in a rocket exhaust is proposed in a joint effort by MetroLaser and Vanderbilt University. Hydroxyl Tagging Velocimetry (HTV) uses an ultraviolet laser to tag a region of the flow with OH molecules, and interrogates them after a short delay with a second laser to obtain velocity from time-of-flight data. The method relies on the dissociation of H2O molecules naturally present in the flow, and thus requires no seeding. Being an all-optical technique, it is not adversely affected by high temperatures or high dynamic pressures. Analyses and experiments conducted during the Phase I effort demonstrated feasibility by showing that OH tag lifetimes in a simulated rocket exhaust environment were sufficiently long to enable accurate determination of tag displacements corresponding to typical rocket exhaust velocities. The method was demonstrated by measuring velocities in the exhaust gases of a laboratory scale burner at temperatures and chemical compositions representative of a H2/O2 rocket exhaust. Design tradeoff studies predicted that at measurement ranges of 20 to 50 feet the accuracies would be from two to five percent. This proposal outlines a plan to develop a prototype HTV instrument and demonstrate it in a rocket engine exhaust.

* information listed above is at the time of submission.

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