High-Fidelity Prediction of Launch Vehicle Liftoff Acoustic Fields

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,947.00
Award Year:
2011
Program:
STTR
Phase:
Phase I
Contract:
NNX11CI36P
Award Id:
n/a
Agency Tracking Number:
100113
Solicitation Year:
2010
Solicitation Topic Code:
T9.01
Solicitation Number:
n/a
Small Business Information
AL, Huntsville, AL, 35805-1944
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
Y
Duns:
185169620
Principal Investigator:
Abhijit Tosh
Principal Investigator
(256) 726-4925
sxh@cfdrc.com
Business Contact:
Silvia Harvey
Business Official
(256) 726-4858
sxh@cfdrc.com
Research Institute:
University of Cincinnati
Yijun Liu
P.O. Box 210072
Cincinnati, OH, 45221-0072
() -
Nonprofit college or university
Abstract
The high-intensity level acoustic load generated by large launch vehicle lift-off propulsion is of major concern for the integrity of the launch complex and the vehicle payloads. The currently practiced computational methods are unable to offer the reliability of both the noise generation mechanism and acoustic environment. In order to uniquely address both of these critical aspects, the proposed approach will unify the physics of noise production with propagation and structural interactions. This method will utilize hybrid LES/RANS modeling established in NASA production flow solvers (Loci-Chem and OVERFLOW) capable of realistic descriptions of flow-acoustic interactions. A non-dissipative acoustic Boundary Element Method (BEM) will be coupled with the well-resolved noise source for high-quality acoustic environment predictions, equipped with the Fast Multipole Method (FMM) for solution acceleration. In Phase I, merits of the proposed approach will be investigated for plume impingement problems. A high-performance simulation architecture, easy user interfaces and post-processing utilities will be developed for complex geometries and efficient large-scale simulations. Phase II efforts will involve refinements and extensive evaluations for high-resolution noise source modeling, transition of mixed speed flow regimes, wave propagation through non-uniform flow, and supercomputing capabilities facilitating new insights into rocket exhaust acoustic loading and comprehensive noise suppression analysis.

* information listed above is at the time of submission.

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