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National Advisory Committee for Aeronautics, Technical Notes - Tables and Charts of Flow Parameters Across Oblique Shocks

The oblique shock—wave equations have been solved for a range of
Mach number in front of the shock from 1.05 to h.0 and for a range of
shock angle from a simple Mach wave to a normal shock. The results of
these calculations are presented in tabular form and include values
for the Mach number in front of the shock, the shock angle, the
deviation of the flow across the shock, the Mach number behind the shock,
the ratio of pressure behind the shock to pressure in front of the
shock, the ratio of density in front of the shock to density behind
the shock, and the change in entropy across the shock. Charts of
several of these parameters are also presented.

When a compression shock occurs in supersonic flow, the flow
across the shock wave undergoes changes in its physical character—
istics. These changes in characteristics of the flow behind the
shock have been calculated in terms of similar characteristics of the
flow in front of the shock from the fundamental shock—wave equations
(reference 1). Calculations of values of some of the parameters most
frequently used in supersonic studies have been presented in refer—
ences 2 and 3. These computations, however, are limited in scope.
More recently, reference A has been published to give a general survey
of the equations, tables, and charts that are continually being used
in research on supersonic flows. The material presented herein
supplements and extends the information of reference A. Because the
nature of these computations is basic and the existence of such data
would serve to avoid repetition of the same calculations in the
future, an attempt has been made to present the results in a form
that has already proved extremely useful for rapid calculations in
the study of supersonic-flow problems and in supersonic design work.