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Early-Design Aeroacoustics Prediction for Distributed Electric Propulsion Vehicles using FlightStream

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC20C0586
Agency Tracking Number: 204887
Amount: $124,988.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: T15
Solicitation Number: STTR_20_P1
Solicitation Year: 2020
Award Year: 2020
Award Start Date (Proposal Award Date): 2020-08-12
Award End Date (Contract End Date): 2021-09-30
Small Business Information
1919 North Ashe Court
Auburn, AL 36830-0000
United States
DUNS: 078301615
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Vivek Ahuja
 (334) 332-6078
Business Contact
 Roy Hartfield
Phone: (334) 444-8523
Research Institution
 Auburn University
141 Engineering Drive
Auburn, AL 36849-5338
United States

 Nonprofit College or University

Research in Flight and Auburn University are proposing to develop a robust tool and methodology to allow the simulation and modeling of acoustic signatures for Distributed Electric Propulsion (DEP) air vehicle concepts in the conceptual design phase. These new tools will enable the study of aeroacoustics in much greater detail and with greater fidelity than heretofore deemed practical in the early phases of design. Early aeroacoustic prediction capability will expose potentially problematic acoustic signatures so that configuration changes, and both active and passive noise control technologies can be introduced during conceptual design, thus resulting in significant cost and schedule efficiencies.In this proposed activity, a simplified acoustic formulation based on the Farassat 1A solution of the Ffowcs Williams-Hawkings (FW-H) Equation will be used. This 1A formulation is a solution of the FW-H equation for thickness and loading noise by integration over the body surface flow, computed by the vorticity-flow solver.It has been shown with Vortex Lattice flow solvers that the above acoustic formulations can lead to substantial savings in complexity and solution times while maintaining a reasonable level of accuracy for early design stages, especially for rotor noise problems. This activity will extend these findings and couple a simple, easy-to-use, lower-order acoustics tool to a higher-order panel solver such as FlightStreamreg;, which is already in use by NASA for DEP aero-propulsion analysisFlightStreamreg; has been developed by Research in Flight as a fast, accurate, flow solver using surface-vorticity on the outer mold line of an aircraft. FlightStreamreg; is strikes the proper balance between modeling fidelity and computational tractability. The FlightStreamreg; unsteady solver will be used to solve for the unsteady aero-propulsive loads on the DEP vehicle. This activity will result in the creation of a conceptual-phase Aeroacoustics Toolbox in FlightStreamreg;.

* Information listed above is at the time of submission. *

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