Dynamic Stability Derivatives for a Flying Wing (Aircraft)

$210.00 Student Discount

  • The problem numerically simulates the Dynamic Stability Derivatives of a Flying Wing Aircraft using ANSYS Fluent software.
  • We design the 3-D model by the Design Modeler software.
  • We mesh the model with ANSYS Meshing software, and the element number equals 4,245,614.
  • We perform this simulation as unsteady (Transient).
  • We use the Mesh Motion and UDF files to define rotational and oscillation motion of the wing.

Special Offers For Single Product

If you need the Geometry designing and Mesh generation training video for one product, you can choose this option.
If you need expert consultation through the training video, this option gives you 1-hour technical support.
The journal file in ANSYS Fluent is used to record and automate simulations for repeatability and batch processing.
editable geometry and mesh allows users to create and modify geometry and mesh to define the computational domain for simulations.
The case and data files in ANSYS Fluent store the simulation setup and results, respectively, for analysis and post-processing.
Geometry, Mesh, and CFD Simulation methodologygy explanation, result analysis and conclusion
The MR CFD certification can be a valuable addition to a student resume, and passing the interactive test can demonstrate a strong understanding of CFD simulation principles and techniques related to this product.



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.


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 Cm Clp Cnq
Value 0.762 0.814 0.0308 0.897



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