High-Fidelity Prediction of Launch Vehicle Liftoff Acoustic Fields

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX11CI36P
Agency Tracking Number: 100113
Amount: $99,947.00
Phase: Phase I
Program: STTR
Awards Year: 2011
Solitcitation Year: 2010
Solitcitation Topic Code: T9.01
Solitcitation Number: N/A
Small Business Information
CFD Research Corporation
AL, Huntsville, AL, 35805-1944
Duns: 185169620
Hubzone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Abhijit Tosh
 Principal Investigator
 (256) 726-4925
 sxh@cfdrc.com
Business Contact
 Silvia Harvey
Title: Business Official
Phone: (256) 726-4858
Email: sxh@cfdrc.com
Research Institution
 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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