NASA SBIR 2020-I Solicitation

Proposal Summary

 20-1- A1.02-5606
 Quiet Performance - Aircraft Propulsion Noise
 Unstructured Overset Hybrid RANS/LES Simulations for Jet Noise Prediction
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Scientific Simulations, LLC
1582 Inca Drive
Laramie, WY 82072
(307) 399-0871

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Dr. Enrico Fabiano
1582 Inca Drive Laramie, WY 82072 - 5007
(307) 761-3829

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Dimitri Mavriplis
1582 Inca Dr. Laramie, WY 82072 - 5007
(307) 399-8717
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

The objective of this proposal is the development and demonstration of an efficient scale-resolving aeroacoustic approach for the prediction of noise generated by installed engine configurations. The development of new engine concepts has traditionally relied on inexpensive low and mid-fidelity methods combined with expensive experimental campaigns. Scale-resolving simulations offer a cost-effective alternative to model testing. In this Phase 1 proposal we seek to demonstrate the efficiency and accuracy of our dual-mesh, dual-solver overset strategy for jet-noise aeroacoustics. An efficient unstructured mesh solver is used to resolve the flow near the nozzle, while our high-order, adaptive, Cartesian mesh DG solver is used to resolve the acoustic waves in the jet-plume region. The DDES approach is used to model the turbulent jet flow. The temporal evolution of the nozzle flow is used as input to a source-time-dominant implementation of the Ffowcs-Williams Hawkings (FW-H) equation to determine the jet’s noise spectra at far-field observers. The acoustic integration will be performed on a permeable surface that encloses the noise-generating turbulent structures in the jet. Additionally, the feasibility of the volume integration of the quadrupole term in the FW-H equation will be investigated. This Phase-1 work will target the prediction of the noise generated by an isolated round jet. The accurate prediction of the noise spectra at far-field observers will demonstrate the feasibility of our high-order, adaptive, overset noise-prediction strategy. The established noise-prediction methodology will be further refined and used in the second phase of this project to predict the noise generated by complex, installed engines configurations. Our overset mesh paradigm is well suited for complex geometries, and our successful implementation of the quadrupole term will resolve the uncertainties in choosing suitable FWH integration surfaces.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The proposed techniques will provide a novel cost-effective high-fidelity tool for jet noise prediction. This is an important application area for the NASA Aeronautics Mission Directorate, since the acceptance of future commercial aircraft depends heavily on reduced environmental impact including take-off and landing noise requirements. Our surface integration FWH code as well as our volume integration quadrupole code will be written in a modular fashion which will be delivered to NASA for inspection and coupling with internal NASA codes.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The high-fidelity, overset jet-noise prediction strategy will complement our ongoing work with lower fidelity RANS-based approaches for design optimization of jet noise metrics.  The developed noise-prediction capability will be marketed by Scientific Simulations LLC to current and potential new customers as a suite of progressively increasing fidelity tools with add-on aeroacoustic capabilities.

Duration: 6

Form Generated on 06/29/2020 20:58:50