Integral methods for computational aeroacoustics

Abstract

New surface integral methods for use in computational aeroacoustics are developed and presented. The methods are derived for moving deformable surfaces. These surfaces may be real, solid surfaces, or computational control surfaces. These methods are derived as extensions to the popular Kirchhoff and Ffowcs Williams-Hawkings methods in use today. The equivalence of these two formulations is also presented. Test calculations are shown to validate the methods for use in jet aeroacoustics studies. However, the methods are presented in a manner that makes them easily applicable in cases where Kirchhoff and Ffowcs Williams-Hawkings methods have been used in the past. (Author)