[en] This document provides the mathematical formulation of the main equations implemented in SDPM, version 1.2.0, December 2024. More details about the mathematical foundation can be found in the series of articles by Morinoand by Dimitriadis et al.
This theory manual and quick reference guide is organized as follows. Section 1 presents the integral formulation of the linearized unsteady potential flow equation. Section 2 presents the panel method used to discretize and solve the boundary integral equation. Section 3 presents the gradients calculation procedure. Section 4 presents the transonic correction methodology. Finally, section 5 gives an overview of the available API as well as its configuration parameters.
Research Center/Unit :
A&M - Aérospatiale et Mécanique - ULiège
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Crovato, Adrien ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale
Language :
English
Title :
SDPM - Source and Doublet Panel Method
Publication date :
December 2024
Creation date :
2024-12
Version :
1.2.0
Technical description :
C++/Python source and doublet panel method with transonic correction to quickly solve unsteady compressible flows for dynamic aeroelasticity.
