The aerodynamics library is part of LADAC and contains functions and Simulink blocks to compute aerodynamics of wings, airfoils, fuselages, ... with different methods. Please refer to the documentation of each content for more information.
- Airfoil
The airfoil project contains models to fit airfoil coefficients with analytic functions and to compute unsteady airfoil aerodynamics with a continuous state-space model. - Common functions
Common functions for aerodynamics models are located here. - Fuselage
This is a very simple aerodynamics model for the fuselage that is based on analytic aerodynamics coefficients functions depending on the angle of attack and the sideslip angle. The functions parameters are estimated by test data available in literature. - Rotorcraft aerodynamics
The rotorcraft aerodynamics contains models to calculate the behavior of rotor disks based on the momentum theory. It also contains a vortex ring state model that is based on real rotor test data. Both steady and unsteady blade element momentum methods are implemented. - Simple wing
The simple wing project is 2-point aerodynamics model for wings that computes reasonable results even for high angles of attack and sideslip angles, where potential flow methods fail. However, for small aerodynamic angles this method is most likely less accurate as potential flow methods. The validation of the simple wing project is currently underway. - VLM Wing
The VLM wing allows the computation of wing aerodynamics with a nonlinear vortex lattice method (VLM) that has no discretization in chord direction. Moreover, it can be coupled with viscous airfoil data. Both steady and unsteady computations are supported. The wing project also contains an interface to structural dynamics models to consider an aeroelastic wing.