Nasser Eddegdag

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.

This research is focused on optimizing aircraft performance by harnessing the principles of avian covert feathers, specifically through the passive control of subsonic laminar incompressible boundary layers on airfoils. The exigency of this study is rooted in the growing need for more aerodynamically efficient aircraft, especially in light of increasing fuel costs and environmental concerns. To achieve this, the study employs a robust mathematical framework that amalgamates asymptotic methods, perturbation techniques, and triple-deck boundary layer theory, aiming for a rigorous quantification of aerodynamic behavior under various flight conditions. Three key parameters are meticulously scrutinized: the corrective parameter b, the flap position s0, and the flap angle β. These parameters are analysed for their impact on the lift (Cl) and drag (Cd) coefficients over a range of angles of attack (α). A notable outcome of this research is the identification of b as a pivotal variable that plays a stabilizing role in the aerodynamic system. Through extensive asymptotical modelling and non-linear stability analysis, it was deduced that b is indispensable for managing lift-to-drag ratios effectively across fluctuating flight conditions. To translate these theoretical findings into practical applications, the study introduces a comprehensive parametric landscape. This landscape serves as a decision-making tool by outlining how the parameters s0 and β behave across varying α scenarios, thereby providing actionable insights for airfoil configuration. Importantly, these results bear significant implications for the aerospace industry. They offer a pathway for the development of more efficient airfoils that promise reduced drag and, consequently, diminished fuel consumption.

The aim of this present work is to develop an improved and more precise analytical modelling of a steady irrotational laminar Shock Wave- Boundary Layer Interaction for weak shockwaves around a thin airfoil at a low incidence in the standard atmosphere. This study adapts the asymptotical modelling of our problem treated by our research team previously and improves the analytical resolution process by integrating the empirical parameter m. Then, confrontation of our analytical model to experimental results obtained through experimentation in Supersonic Wind Tunnel AF300. And finally, a CFD numerical simulation in ANSYS Fluent R13 was conducted in order to validate our model, followed up by a statistical study in SPSS taking into consideration analytical and numerical results in order to establish the exact analytical expression of m for each airfoil depending on upstream Mach numbers .The comparison of results obtained from the numerical, experimental and analytical confrontations of our improved and previous models showed promising results and greatly decreased the approximation errors obtained in our previous studies.