Transonic shockwave/boundary layer interactions on NACA 5 series -24112
Pages : 629-634, DOI:http://Dx.Doi.Org/10.14741/Ijcet/Spl.2.2014.120
The present paper reports theoretical and computational study of interaction of a shockwave with a boundary layer. This type of shockwave boundary layer interaction describes a shockwave interaction with a boundary layer induced by another shockwave. Geometrical shock dynamics is used for theoretical analysis of the shockwave and boundary layer interaction. This paper gives a general understanding of the aerodynamic processes that occur in and around SBLIs, concentrating as much as possible on the physics of these flows. Aerodynamic loads are estimated to explain which factors determine their structure under a variety of circumstances and also show how they impact on other parts of their flowfield, influencing parameters such as the drag, the surface flux distributions, and the overall body flow. The data show that weak shock waves induce an unsteady pressure distribution that can be predicted quite well, while stronger shock waves cause complex frequency-dependent distributions due to flow separation. It demonstrates how the present state of our understanding has resulted through contributions from computational fluid dynamics (CFD). Because of their significance for many practical applications, SBLIs are the focus of numerous studies spanning several decades. Hence, there is a considerable body of literature on the subject.
Keywords: Shockwave, Boundary layer, Airfoil, Interactions.
Article published in International Conference on Advances in Mechanical Sciences 2014, Special Issue-2 (Feb 2014)