NASA SBIR 2018-II Solicitation

Proposal Summary

 18-2- A1.04-5483
 Supersonic Technology - Reduce Take-off and Landing Noise
 Optimization of Supersonic Jet Noise Using a Reynolds-Averaged Navier-Stokes Approach
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. Zhi Yang
1582 Inca
Laramie, WY 82072 - 5007
(757) 650-0862

BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Dimitri Mavriplis
1582 Inca
Laramie, WY 82072 - 5007
(307) 399-8717

Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

The objective of this proposal is the development and demonstration of a cost-effective high-fidelity aeroacoustic design tool for future commercial supersonic nozzle designs and installations. Although eddy-resolving  CFD methods for computing high-speed jet noise are available, such methods are computationally expensive and are currently deemed impractical for use in a design optimization loop. On the other hand, the prediction of turbulence generated noise using the Reynolds-Averaged Navier-Stokes (RANS) equations provides a less accurate but more cost-effective approach for practical design problems, wherein the turbulence length and time scales needed to model the local noise source terms can be extracted from the RANS turbulence model solution, as performed by the NASA JeNo code. The objective of this project is to develop a tightly coupled practical RANS-based jet-noise aeroacoustic analysis and design optimization capability which can be leveraged by government and industrial customers to better understand and design efficient propulsion systems that meet well defined and accepted noise metrics. The approach consists of developing an exact discrete adjoint method for a tightly coupled RANS-acoustic prediction method in order to provide sensitivities for gradient-based aerodynamically constrained acoustic optimizations. This capability will be demonstrated on realistic nozzle configurations including single and dual stream chevron nozzles, and marketed to government and industrial customers in the aerospace industry.

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

The proposed technique will provide a novel tool for enabling the design of supersonic nozzles optimized for reduced far-field noise signatures. This is an important application area for NASA ARMD, since the acceptance of future commercial supersonic aircraft depends heavily on reduced environmental impact. The optimization approach will be developed in a modular fashion and will be easily transferable to NASA in-house RANS codes which incorporate an adjoint capability such as FUN3D.

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

The jet noise optimization capability will be incorporated into the simulation and design tools developed by Scientific-Simulations  and will be marketed to existing and new customers. The approach is seen as a natural extension of the various multidisciplinary adjoint capabilities already developed at Scientific Simulations, and will enable new applications in high-speed jet noise optimization.


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