Dynamic Stability Derivatives for a Flying Wing (Aircraft)

Description:

In this project, we aim to obtain dynamic stability derivatives for a flying wing aircraft. In process of designing a flying wing due to the absence of horizontal and vertical tail regular ways to calculate derivatives and stability analysis is not often very easy.

In that case with ANSYS fluent software and applications of CFD in flight dynamics we can obtain those derivatives. In this simulation, we developed a UDF file to model a UAV motion. The UAV is flying in a subsonic region with Mach 0.6 in sea level altitude.

The geometry is designed in ANSYS Design Modeler software. In addition, an unstructured mesh grid is generated using ANSYS Meshing software. As a result, 4,245,614 cells were generated.

Methodology: Dynamic Stability Derivatives for a Flying Wing Aircraft

Mesh motion and UDF files have been used to simulate aircraft motion. the velocity is 0.6 Mach number and the operating pressure is 101235 pa, simulation starts from zero degree angle of attack and a forced oscillation has been modeled.

Results:

As the results obtain the rate change of Cm and Cl along time, with this data the derivatives are calculated in the table below:

Derivative	Cmq	Cmἀ	Clp	Cnq
Value	0.762	0.814	0.0308	0.897