Design Cycle Prediction Software for Wing-Strut Junction Flow Noise

NASAs Advanced Air Transport Technology Project has worked with industry over the last decade to develop airframe/propulsion concepts and associated technologies to enable transformative air travel for future generations. Techsburg and AVECs proposal Design Cycle Prediction Software for Wing-Strut Junction Flow Noise addresses a technology analysis gap in the development of a leading airframe concept, the Transonic Truss Braced Wing (TTBW) aircraft. The aeroacoustic signatures of the large bracing strut and jury member features of this configuration need to be studied with appropriate modeling to enable design cycle input based on far field noise estimates of these features. Building on Phase I success, we propose to produce a database of hemisphere noise levels (1/3 octave band) using PowerFLOW CFD, with an accompanying model based on machine learning for design cycle trades of this noise source. Phase II will conclude with delivery of the reduced-order software tool Wing-Strut Broadband Acoustic Model, WiSBAM. NASA’s Advanced Air Transport Technology Project has worked with industry over the last decade to develop airframe/propulsion concepts and associated technologies to enable transformative air travel for future generations. This proposal addresses a technology analysis gap in the development of a leading airframe concept, the Transonic Truss Braced Wing (TTBW) aircraft. The aeroacoustic signatures of the large bracing strut and jury member features of this configuration need to be studied with appropriate modeling to enable design cycle input based on far field noise estimates of these features. Techsburg and AVEC will develop and deliver the Wing-Strut Broadband Acoustic Model (“WiSBAM”) a first generation design cycle wing-strut junction broadband noise model utilizing PowerFLOW predictions and machine learning. A neural network-based approach will be used for modeling using machine learning to produce rapid 1/3 octave band noise results for a hemisphere around an isolated wing junction, enabling rapid noise predictions for advanced truss-braced or strut-braced aircraft concepts. Results will be compared to wing self-noise models to assess relative source strength of wing-strut noise compared to other typical airframe sources (flap, slats, trailing edge, landing gear, etc.). Phase II Deliverables: Year 1 beta code followed by Year 2 final code at project end. A primary goal is output of acoustic data suitable for use within ANOPP2 and similar acoustic prediction tools.

Design cycle modeling and understanding of junction flow noise is key in completing the aeroacoustic characterization of the Transonic Truss Braced Wing configuration. This approach can be easily integrated into existing aeroacoustic software frameworks such as ANOPP2, and can be extended to include sources such as tail empennage junctions, antenna installations, landing gear (fixed gear especially), and external store hardpoints. Other engineering areas include surface and underwater ocean vehicles, rotating fan shroud modeling, ventilation systems, automotive industry, and design of architectural and civil engineering features such as bridge piers or buildings that form de facto “wing-body” junctions within the water or atmosphere that flows around them.

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