Abstract:

ESDU AERO S.00.03.08 treats the two-dimensional supersonic flow expanding about a solid boundary in which the Mach waves are straight and the flow velocity and direction are constant along any Mach line. Such simple-wave flow is found downstream of regions of uniform flow, and the flow near a thin aerofoil with attached shock waves can be closely approximated by it. A particular case is expansion around a sharp corner; see ESDU AERO S.00.03.27 for an example on using the Mollier chart to solve such a flow. Graphs are provided of the Mach angle as a function of local Mach number and, using the equation for the deflection angle given in ESDU AERO S.00.03.06, of flow deflection angle as a function of Mach number and the ratio of specific heat capacities. An equation is given for the maximum flow deflection for expansion from Mach 1.

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