  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.
