Summary COMPRESSIBLE FLUID FLOW - NORMAL SHOCKS AND GOVERNING EQUATIONS FOR COMPRESSIBLE FLOWS

This report first explores the use of normal shock relations to determine the effect of Mach number ahead of the shock on flow properties in the form of their ratios. The report tackles property ratios such as the pressure ratio, temperature ratio, total pressure ratio, and even the Mach number behind the shock. This is done by creating a MATLAB code that calls a function to calculate these property ratios and plots them against the Mach number ahead of the shock, M1. The values returned are compared to calculated values by Anderson et al[1] and they agree well with the data. The Hugoniot curve is also considered as an alternative for calculating flow properties behind the shock using another MATLAB code that plots the curve and uses a point consisting of flow properties ahead of the shock to draw a line that intersects another point on the curve, and this point reveals flow properties (i.e, pressure, and specific volume) behind the shock. The value obtained also is found to agree with the normal shock relations employed in this report as well as the values from Anderson’s tabulated data. Finally, the report simplifies the flow governing equations of continuity, momentum, and energy over a control volume in a jet ejector and uses these simplified equations to calculate the exit flow properties of the jet mixture.