Version 1.2

Version 1.2 - Transonic correction and analytical gradients

This version mainly features a transonic solver and analytical pressure derivatives.

Changes

• Add transonic correction
• Add analytical gradients
• Add feature to deform the body
• Fix calculation of motion-induced velocity and unsteady pressure
• Refactor APIs and utilities

Notes

Transonic correction
The unsteady pressure solution can now be corrected by higher-fidelity data (typically obtained from CFD) to include transonic and viscous effects.
Analytical gradients
Although CoDiPack works well, its memory footprint is too large for practical unsteady cases (see #6). Analytical pressure and aerodynamic forces gradients have therefore been implemented so that flutter constrained optimization can be performed within a reasonable computational time.
Body deformation
The body nodes can now be set to new positions for aeroelastic and optimization purposes.
Formulation fixes
The calculation of the surface velocity induced by a rigid pitching motion has been corrected to use original instead of compressible coordinates. Additionally, a mistake in the calculation of the unsteady pressure coefficient has been fixed.
Refactoring
The default values in the API have been refactored. The slicing utility now also outputs z-coordinates.

Tests

• Ubuntu 22.04 (gcc 11, python 3.10)

README.md

 # SDPM
-SDPM is an open-source C++/Python, unsteady compressible source and doublet panel method, developed at the University of Liège by Adrien Crovato and Grigorios Dimitriadis, during the academic years 2022-2023.  
-SDPM is currently capable of rapidly solving steady or unsteady compressible subsonic flows on isolated or multiple wings.
+SDPM is an open-source C++/Python, unsteady compressible source and doublet panel method, developed at the University of Liège by Adrien Crovato and Grigorios Dimitriadis, during the academic years 2022-2024.
+SDPM is currently capable of rapidly solving steady or unsteady compressible subsonic flows on isolated or multiple wings, as well as calculating the aerodynamic forces gradients. Furthemore, the code is interfaced with [OpenMDAO](https://openmdao.org/) so that aeroelastic computations and optimization can be easily carried out.  
 
 ## Main features
 * Cross platform (Windows and Unix) C++/Python code
 * Physical model
-  - unstructured quadrangle meshes for 2D geometries using [gmsh](https://gmsh.info/)
+  - unstructured quadrangle meshes for 3D geometries using [Gmsh](https://gmsh.info/)
   - steady and unsteady flows
-  - subsonic compressile flows
+  - subsonic compressile flows with transonic correction
 * Numerical methods
   - linear algrebra using [Eigen](http://eigen.tuxfamily.org/)
+  - reverse automatic differentiation using [CoDiPack](https://github.com/SciCompKL/CoDiPack)
 
 ## Documentation
 Detailed build and use instructions can be found in the [wiki](https://gitlab.uliege.be/am-dept/sdpm/wikis/home).
 
 ## References
+Crovato Adrien, [SDPM - Source and Doublet Panel Method](https://hdl.handle.net/2268/324280), Technical note, University of Liège, 2024.  
 Sanchez Martinez Mariano and Dimitriadis Grigorios, [Subsonic source and doublet panel methods](https://hdl.handle.net/2268/291174), Journal of Fluids and Structures, 2022.