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.