Towards Interference Corrections for Three-Dimensional Models in Kevlar-Walled Anechoic Test Sections

As part of a continuing development effort on Kevlar-walled anechoic test sections, this paper addresses the aerodynamic corrections of such test sections for the case of threedimensional flow over wings. The correction method employs a panel method to simulate the porous, flexible boundary conditions of the Kevlar walls. This paper extends the panel method which previously was only for use in two-dimensional flow situations to the case of three-dimensional flow. Subsequently, evaluation of the three-dimensional correction method is presented based on results obtained at the Japan Aerospace Exploration Agency (JAXA) including side-by-side tests of wings in both solid-wall and Kevlar-walled test sections. New measurements of test section wall pressure distributions and anechoic chamber pressures that validate the correction method are also included. Our goal is that with the increasing fidelity of aerodynamic corrections, Kevlar-walled test sections will become as useful for aerodynamic testing as they are for aeroacoustic testing.