Shock polar explained

The term shock polar is generally used with the graphical representation of the Rankine–Hugoniot equations in either the hodograph plane or the pressure ratio-flow deflection angle plane. The polar itself is the locus of all possible states after an oblique shock. The shock polar was first introduced by Adolf Busemann in 1929.^[1]

Shock polar in the (φ, p) plane

The minimum angle,

\theta , which an oblique shock can have is the Mach angle \mu = \sin ^{-1} ( 1 /M) , where M is the initial Mach number before the shock and the greatest angle corresponds to a normal shock. The range of shock angles is therefore \sin ^{-1} ( 1 /M)\leq\theta\leq\pi / 2 . To calculate the pressures for this range of angles, the Rankine–Hugoniot equations are solved for pressure:$$\backslash frac\; =\; 1\; +\; \backslash frac\; \backslash left(M^\backslash sin^\backslash theta\; -\; 1\backslash right)$$To calculate the possible flow deflection angles, the relationship between shock angle \theta and \varphi is used:$$\backslash tan\backslash varphi\; =\; 2\backslash cot\backslash theta\backslash frac.$$Where \gamma is the ratio of specific heats and \varphi is the flow deflection angle.

Uses of shock polars

One of the primary uses of shock polars is in the field of shock wave reflection. A shock polar is plotted for the conditions before the incident shock, and a second shock polar is plotted for the conditions behind the shock, with its origin located on the first polar, at the angle through which the incident shock wave deflects the flow. Based on the intersections between the incident shock polar and the reflected shock polar, conclusions as to which reflection patterns are possible may be drawn. Often, it is used to graphically determine whether regular shock reflection is possible, or whether Mach reflection occurs.^{[2] [3]}

References

• Book: Chapman, C.J. . High Speed Flow . . 2000 . 978-0-521-66169-0 .
• Book: Anderson, John D. Jr. . Fundamentals of Aerodynamics . 1984 . 3rd . . January 2001 . 978-0-07-237335-6 .

Notes and References

1. Busemann, A. 1929. Verdichtungsstosse in ebenen Gasstromungen. In Vortraye aus dem Gebiet der Aerodynamik, Aachen, ed. A. Gilles, L. Hopf, T. von Karman, p. 162. Berlin: Springer-Verlag
2. Book: Ben-Dor, Gabi . Shock Wave Reflection Phenomena . 2nd . . 2007 . 978-3-540-71381-4 .
3. Web site: Transition between Regular Reflection and Mach Reflection in the Dual-Solution Domain . 2007 . 2010-08-13 .