Improved Analytical/Statistical Modelling of the Shock Wave-Laminar Boundary Layer Around a Thin Airfoil Standard Atmosphere Case

TL;DR

This paper develops an improved analytical model for shock wave-laminar boundary layer interactions around thin airfoils, validated through experiments, CFD simulations, and statistical analysis, reducing previous approximation errors.

Contribution

It introduces an empirical parameter m into the analytical model, enhancing accuracy and validation against experimental and numerical data.

Findings

Reduced approximation errors compared to previous models

Validated analytical model with experimental and CFD data

Established empirical parameter m for different Mach numbers

Abstract

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.