Large Eddy Simulations of Hot Supersonic Jets for Aeroacoustics

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-09-C-0368
Agency Tracking Number: N09A-008-0009
Amount: $70,000.00
Phase: Phase I
Program: STTR
Awards Year: 2009
Solitcitation Year: 2009
Solitcitation Topic Code: N09-T008
Solitcitation Number: 2009.A
Small Business Information
Cascade Technologies Incorporated
1330 Charleston Road, Mountain View, CA, 94043
Duns: 179576715
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Shoreh Hajiloo
 General Manager
 (650) 691-6067
Business Contact
 Parviz Moin
Title: President
Phone: (650) 224-4882
Research Institution
 California Institute of Technology
 Tim Colonius
 1200 East California Boulevard
Pasadena, CA, 91125
 (626) 395-4021
 Nonprofit college or university
The technical objective of this proposal is to develop and demonstrate LES capability to predict hot jet noise at supersonic operating conditions of tactical aircrafts. We also propose an LES based non-linear instability method (NPSE) to provide reduced order, physics-based models for noise generated by large-scale turbulent structures in hot jets. CASCADE’s unstructured solver, CHARLES, will be used for LES noise prediction. To achieve this, fully compressible N-S equation with dynamic SGS model will be solved in the near field, this data is then used to calculate the far field noise using acoustics projection methods. Near-field LES results will also provide mean flow fields and amplitude of instability waves required for NPSE modeling. Careful validation of the flow field and noise predictions will be conducted in close partnership with an industry partner (UTRC). In phase I, the feasibility of proposed methods will be demonstrated using pressure-matched hot jets with round nozzles. In phase I option, we extend the complexity to chevron nozzles and pressure-mismatched operating conditions. In Phase II, we focus on realistic nozzle geometries and engine configurations. In addition, the effect of airframe will be integrated in noise calculations.

* information listed above is at the time of submission.

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