Investigation of viscous supersonic laminar flows around F-16 airfoil: experimental, numerical, and analytical approaches

Abstract

Abstract This research paper primarily focuses on the behavior of viscous supersonic laminar flows around the F-16’s NACA 64A-204 airfoil, while also extending its scope to Shock-Wave/Boundary-Layer Interactions. The aim is to evaluate and compare methodologies for accurately characterizing these crucial aerodynamic phenomena. A unique experimental setup was developed, featuring mock-ups of F-16 airfoil equipped with pressure taps, and tested in the Supersonic Burst Wind Tunnel AF300. Computational Fluid Dynamics simulations were conducted using Ansys Fluent 2022 R2 and were supplemented by our previously established analytical model was adapted to our specific airfoil case, following calculations of the wing section equation. Key aerodynamic parameters such as lift coefficient, drag coefficient, Local Mach numbers, and the characteristics of the shock waves formed around the airfoil were examined. The study validates the NACA 64A-204 mock-up, with average errors for key parameters and 1st and 2nd Pressure Taps between the three adopted approaches remaining below 2.5%. The findings contribute valuable insights into the fundamental physics of viscous supersonic laminar flows, offering immediate applications to the design of high-speed aircraft and other advanced aerospace technologies. Additionally, the validated mock-up enhances the research capabilities of the Supersonic Burst Wind Tunnel AF300. Ultimately, this study serves as a foundational reference for optimizing aerodynamic surfaces, thereby facilitating advancements in key vehicle performance metrics such as manoeuvrability and fuel efficiency.