Version 1.0 - Unsteady compressible source and doublet panel method
USCSDPM, shortened SDPM, is an implementation of the original source and doublet panel method proposed by Morino (L. Morino and P. Chen, Steady and oscillatory subsonic and supersonic aerodynamics around complex configurations, AIAA Journal, 1975) and revisited by Dimitriadis (M. Martínez and G. Dimitriadis, Subsonic source and doublet panel methods, Journal of Fluids and Structures, 2022). The main purpose of SDPM is to provide steady and unsteady pressure distributions on fixed and moving wings. The code is currently capable of computing steady or unsteady, compressible or incompressible flows on isolated or several wing surfaces.
Features
C++ code interfaced in Python using SWIG
Steady or unsteady flows caused by forced harmonic pitching motion of the boundary
Incompressible or compressible flows
Isolated or multiple wings
Limitations
Flow are currently limited to the compressible subsonic, but not transonic regime
No gradient computation method is currently featured
Only rigid pitching motion can be currently imposed on the moving boundary
These limitations will be addressed in future developments.
