  This research paper presents a comprehensive investigation into the behavior
of viscous supersonic laminar flow and the Shock Wave- Laminar Boundary Layer
Interaction (SWBLI) around the F-16 laminar NACA 6-series airfoil NACA 64A204.
The study aims to establish and compare different methods for accurately
describing these complex phenomena, which are of significant importance in the
development of advanced aerospace technologies. To achieve this objective, a
unique approach was adopted, involving the design and production of a mock-up
F-16 airfoil equipped with pressure taps for use in the supersonic burst wind
tunnel AF300. The mock-up was then experimentally tested, and the obtained data
were analysed using numerical simulations with Ansys Fluent and a theoretical
model based on a previously established analytical SWBLI model. The results
obtained from the experimental, numerical, and analytical analyses validate the
designed NACA 64A204 mock-up to a great extent. The study provides valuable
insights into the physics of viscous supersonic laminar flow and SWBLI,
contributing to a better understanding of these phenomena. The findings of this
study will have important applications in the design of high-speed aircraft and
other advanced aerospace technologies.
