EDA’s engineers continuously seek for cost and time effective solutions for design projects and utilize all levels of computational tools ranging from basic engineering methods to advanced high fidelity solvers depending on design requirements using their rich experience. All design and research projects are managed by using project management, version control and bug or failure report software installed in company servers. By means of systematic scheduling backup system and secured network infrastructure, data loss or information transfer is prevented. EDA’s design and analysis capabilities can be summarized as follows:

Store Separations with Flight Mechanics Coupling

The estimation of the influence of an external store mounted under the wing to the aircraft performance is very significant; besides it is also crucial to determine its safe separation during the flight. The separation of the newly designed store in its first test flight may lead to a disaster. For this reason, the question of safe-separation must be solved and proven by means of wind-tunnel tests before the flight tests. However, it is preferable to minimize the number of very expensive tests for which not every wind tunnel is appropriate. EDA has moving body solution capabilities suitable for wing separation.

Example : An advanced store separation case solved with CAEedaTM


(a) Unstructured mesh with tetrahedral elements 


(b) Distribution of velocity on  surface during store separation


(c) Comparison between solution and experimental results, showing that at the solution matches the experiments

Figure 6 Solution of the store separation case 

Solid Fluid Interactions

Prediction of nonlinear aeroelastic flutter phenomena requires the coupled solution of fluid and solid (structural) dynamics equations. In the approach used by CAEedaTM the fluid problem is solved using computational fluid dynamics (CFD) code and the structural dynamics problem is solved by a computational structural dynamics (CSD) code.  The codes communicate with each other at the fluid-solid interfaces, where the nodes may or may not match, since typically coarser meshes are used for solids and denser meshes used for fluids. While this multidisciplinary approach is used for aeroelastic flutter here, it is also suitable for other applications such as aero-heating and aero-acoustic problems

Example: Solution of an aeroelastic flutter example solved in CAEedaTM.  Fluid-Structure interaction may produce flutter that would cause the failure of an airplane wing. The plot shows that the solution matches with the experimental results (Figure-7).

Figure 7: Fluid-structure interaction simulations solved in CAEedaTM for flutter analysis of an airplane wing (AGARD Wing 445.6 test case).