fuselage

Discretized Aerodynamic Model for Fuselages

This program discretely resolves the aerodynamics of the fuselage along the centerline. This is especially important for the simulation of aeroelastic models; the coupling with a structural dynamics model is supported. This aerodynamic model is based on basic equations from [1].

Motivation

For flight dynamic simulations, the fuselage often cannot be neglected when calculating aerodynamic forces and moments. The fuselage mainly contributes an aerodynamic pitch and yaw moment. However, it also happens that the fuselage generates a non-negligible lift and lateral force. A fuselage model then influences the trim point and dynamic characteristics. This fuselage model is discretely resolved along the centerline and offers the possibility to be coupled with a structural model. Furthermore, this discrete model offers the possibility to consider simple aerodynamic interactions between fuselage and wing.

Installation

• You need LADAC

Examples

General

Start the example by running fuselage_example.m:

fuselage_example

Two figures should appear: lift distribution along the centerline and geometric visualization of the fuselage.

Simulink

Start the Simulink example by running:

fuselage_lib_example_init

Take a look at the Simulink model. For information about the inputs and outputs, take a look at the Matlab function documentation (see How to use).

How to use

You can define your desired fuselage:

• Take a look at fuselageCreate. You will see that you need to specify a parameters file. Therefore, you should use the fuselage_params_default file as a template.
• Make a copy of fuselage_params_default and name it fuselage_params_myfuselage.
• Adjust the parameters according to the documentation/comments.
• Now open the script fuselage_example and change the input variables of the function call fuselageCreate. Amend it to the name given to your parameter file.
• Run fuselage_example again and you will see the geometry of your fuselage as well as the lift distribution along the centerline.
• For more information, please study the scrip fuselage_example.
• All functions are documented. Take a look at them if you have questions.

Literature

[1] Schlichting, H., & Truckenbrodt, E. (2001). Aerodynamik des Flugzeuges. Zweiter Band: Aerodynamik des Tragflügels (Teil II), des Rumpfes, der Flügel-Rumpf-Anordnung und der Leitwerke. 3. Auflage. Springer-Verlag Berlin Heidelberg.