Print Email Facebook Twitter Computational Noise Prediction using LES and the Kirchhoff Method Title Computational Noise Prediction using LES and the Kirchhoff Method Author Schütz, Dennis (TU Delft Aerospace Engineering) Contributor Hickel, Stefan (mentor) Munz, C.-D. (mentor) Degree granting institution Delft University of Technology Programme Aerospace Engineering Date 2017-10-02 Abstract The multi purpose CFD solver INCA is currently used for ow calculations on a variety of industrial and research projects. Supporting multiple discretization schemes in space and time, many engineering problems can be solved including turbulence, transition, multi-phase systems, combustion, cavitation and supersonic effects. The objective of the present work is the extention of the solver's capabilities to aeroacoustic simulations of the farfield noise. While the basic methods for the calculation of ow induced noise didn't change during the last three decades, today's accurate CFD-methods together with the available computational power offer a new field of application for aeroacoustic methods. The acoustic wave propagation in the nearfield can be accurately calculated using LES methods while the acoustic transport to the farfield is conducted using analytical methods. Following a literature research on the available aeroacoustic methods, a suitable procedure will be chosen for the calculation of the farfield acoustics, using the nearfield solution of the built in LES method. The derivation of the integral form of the according method will be covered in detail and transformed to the frequency domain. Since the acoustics calculation is to be conducted during processing in order to avoid the storage of large amounts of data, the discrete fourier transform will be derived from the integral form for varying time steps of the simulation. The implementation structure and the usage of the acoustic's module will be documented. The code will be validated using different 2D and 3D test cases and according conclusions will be drawn. Finally, the aeroacoustic _eld of the NACA0012 airfoil will be investigated and compared to available experimental results. To reference this document use: http://resolver.tudelft.nl/uuid:5bb6ed94-7d72-4faa-b5db-b522da80de99 Part of collection Student theses Document type master thesis Rights © 2017 Dennis Schütz Files PDF Schuetz_D..pdf 10.2 MB Close viewer /islandora/object/uuid:5bb6ed94-7d72-4faa-b5db-b522da80de99/datastream/OBJ/view