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Completed TRL 2 (started at 1, targeting 2)
We propose Project SWaP-SIM3D to address the problem size bottleneck in frequency domain (FD) computations of wave propagation in nonuniform mean flows via algorithmic improvements to allow high-fidelity parameter studies in practical aerospace applications that require orders of magnitude increase in computed degrees of freedom (DOF). The advantage over conventional, time-domain simulations is orders of magnitude higher efficiency & the breakthrough relative to direct solution technique in existing FD codes for multi-dimensional instability wave analysis is up to 3 orders of magnitude increase in problem size (DOF) during current effort and 6 orders of magnitude eventually. Multiple NASA projects (AATT, CST, HTP, RVLT) will gain high-fidelity prediction capability after project completion, including laminar-turbulent transition, aeroacoustic & vibration simulations related to airframe/propulsive sources of noise, and selected aspects of flow control, buffet onset, stall, etc. We anticipate technical risk due to potential sensitivity of convergence & accuracy of the iterative algorithms to configuration details, leading to reduced robustness of the proposed approach, but also expect to overcome the difficulty by addressing specific characteristics of the stalled convergence, and thus to achieve the target outcome of developing a robust and efficient, high-fidelity prediction capability that is highly useful in practical applications. The projected outcomes and opportunities for cross-cutting improvements are supported by preliminary investigation by the team, which combines experience in both algorithmic and application aspects.
Besides establishing the feasibility of iterative solvers for parameter studies of wave propagation problems, a successful effort will lead to prototype capability for both single block and multiblock structured mesh configurations with O(106)–O(108) degrees of freedom, allowing the solution of fully 3D problems of moderate complexity. The current effort will serve as a steppingstone for future work on unstructured grid implementations, chemical reaction effects, and generalized solvers that account for numerous wave components, such as multiple frequencies and nonlinear interactions among them. The outcome of this development could be plugged into current NASA capability for high fidelity transition analyses & provide a unique, new capability for advanced aeroacoustic predictions, to address specific applications under multiple NASA projects, with a modest effort on integration and user interface development. Lacking such high-fidelity prediction tools would result in slower and less reliable development of greener technologies for both subsonic and high-speed transports, such as increased laminar flow (AATT, CST, HTP) and effective engine noise shielding via propulsion-airframe integration (AATT, AAM), as well as a higher risk of losing technical leadership in advanced tool development (CST, HTP), putting the US at a competitive disadvantage in the long run. This cross-cutting research will benefit several technological areas connected to energy efficiency and noise pollution, allowing the resulting capability to be used in multiple NASA initiatives.
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