Experimental Investigation on Steady Shock Structures in an Axisymmetric Supersonic Intake Using Image Processing Technique

A Matlab Code was written in the field of image processingto study all kinds of shock structures in an axisymmetricsupersonic intake for different conditions of the flow field.The purpose is to define different semiempirical correlationsthat illustrate the shock structure changes with respect to thedifferent operating conditions using image processing ofdifferent shadowgraph images of the flow field around theintake. Different experimental data are used to provide somewell-posed nondimensional experimental relations thatcould be used in different cases. The effect of mass flowratio through the intake duct on the shock position wasfound to be very significant. As mass flow ratio increased,the normal shock were moved toward the intake and gotthinner to pass through the intake throat. The curved shockwhich is defined by a hyperbola relation in each experiment,would get less eccentric as mass flow ratio increases.