Reduced-Order Inflow Model for Propeller-Airframe Flow Interaction Noise Assessment

The efficient modeling of acoustic interaction between wake generated by lifting and control surfaces, with a propulsive flowfield of a pusher propeller configuration forms the focus of this proposed SBIR project. Modeling these effects involves complex, high fidelity, and high performance computing simulations that tend to be cumbersome and time consuming. Multiple realizations of coupled response is needed for practical problems in order to explore the design space, quantify interaction mechanisms, develop control algorithms or perform design optimization. Recent developments in reduced basis methods provide means to perform large and expensive multi-parameter simulations using dramatically reduced computational effort (sometimes several orders of magnitude), while not compromising on the accuracy of the physical model (no approximations in physics).We propose here a systematic maturation of reduced basis modeling techniques in airframe (specifically, tail) aerodynamics and pusher propeller configurations in both fixed wing and rotor aircraft. We will explore the use of interacting low dimensional models, in a single multiphysical framework. This work will be based on recent developments at HyPerComp and elsewhere in the model reduction for unsteady nonlinear processes in gas dynamics. Phase-I research will establish a baseline methodology, to be extended and demonstrated in a potential future phase.