Two-Step MILES/MIDES Methods for Aircraft Aeroacoustics Analysis

This research is dedicated to the development of a high fidelity analysis tool to  accurately predict the full aircraft aeroacoustic field in subsonic, transonic,and supersonic regimes. Innovative two-step, implicit Monotonically Integrated LES (MILES) and DES (MIDES) methods for jet and airframe (cavity) noise, respectively, will be developed through this SBIR. An accurate and very efficient reduced order model will also be constructed to reduce the computational cost. The far field noise will be resolved by the permeable surface Ffowcs Williams-Hawkings (FW-H) method. In addition, parallelization will be applied in the final modular code to further improve the computational efficiency. In Phase I, the development will emphasize the state-of-the-art two-step MILES method. Appropriate flux limiters, boundary conditions, and incoming excitation flow conditions will be investigated for the MILES method. Based on the resulting formulations, a CAA software package will be developed to demonstrate the feasibility of the approach through benchmark testing. Meanwhile, the reduced order model will be formulated to achieve an accurate and efficient aeroacoustic solution. BENEFITS: The proposed aeroacoustics analysis tool development will benefit both military and civil aviation applications. The innovative aeroacoustics analysis methodology developed from this SBIR will significantly enhance modern aircraft design, testing, and operations.