ESDU AERO 00.03.28 gives equations for the downstream Mach number, and the ratios across the shock of static pressure, total pressure, density and temperature, all as functions of upstream Mach number. Using those equations, graphs of downstream Mach number, and the ratios of temperature, static pressure and total pressure across the shock are plotted against upstream Mach number from 1 to 4 and for a range of specific heat capacity ratios from 1 (to aid interpolation) to 1.67. Another graph plots the ratio of downstream total pressure to upstream static pressure against the same ranges of upstream Mach number and specific heat capacity ratio.