Stability Analysis and Aerodynamic Validation of a Supersonic Rocket Using Ansys Fluent Software

“Ansys tools have been a game changer in advancing our work in rocketry. With Ansys Fluent software, we conducted high-fidelity simulations that bridged the gap between theoretical analysis and experimental testing. The comprehensive documentation, case studies, and theoretical resources were invaluable in helping us fully grasp the software’s capabilities. In rocketry, mitigating failure and managing risk begins with a deep understanding of vehicle behavior, and Ansys made that possible for us.”

— Félix Pobeda
Head of Simulations / TopAéro

Engineering Solutions 

The Ansys DesignModeler tool was employed to generate the computational domain and prepare the geometry for analysis. The Ansys Meshing application was then used to create the spatial discretization with localized refinement near critical aerodynamic features. Finally, Fluent software served as the main solver for flow simulations.

Prior to running the simulations, TopAéro had limited information regarding the extent of fin masking caused by the deployed airbrakes. By extracting the pressure coefficient distribution on each fin, determining the center of pressure, and performing sensitivity analyses with respect to Mach number and angle of attack, they were able to assess whether the rocket would maintain nominal aerodynamic stability.

The versatility of the tools available in the Fluent Results tab proved invaluable. These features enabled the team to explore and visualize multiple physical parameters simultaneously to gain an understanding of their respective contributions within a single set of simulations.

Key features and capabilities included:

• Surface and contour plotting of aerodynamic variables, such as pressure coefficient, wall shear stress, and Mach number
• Force, moment, and center of pressure reports

Benefits

The team was able to validate aerodynamic stability prior to manufacturing, thereby avoiding costly and time-consuming physical testing.

• Design iteration time was reduced by approximately 30%, as multiple configurations could be assessed virtually.
• Optimal airbrake deployment ranges were identified, ensuring effective drag modulation without compromising stability
• The team’s understanding of aerodynamic interactions was improved, including concepts such as fin masking and asymmetric pressure distribution, thereby strengthening members’ capability to design control surfaces for future rockets.
• The team gained experience with computational fluid dynamics (CFD) workflows, turbulence modeling, and post-processing techniques in alignment with industry standards.
• Decision-making during the design phase was enhanced, as quantitative simulation results informed design reviews and mission planning.

The results obtained through engineering simulation gave the team the confidence necessary to validate the aerodynamic configuration prior to fabrication and flight testing. The rocket is scheduled for launch in July 2026 during a French intercollegiate rocketry competition, and the team’s simulation outcomes confirmed that it can safely operate under this configuration.