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Shock polar : ウィキペディア英語版
Shock polar
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.
== Shock Polar in the (\varphi ,p) Plane ==

The minimum angle, \theta, which an oblique shock can have is the Mach angle \mu =\sin^(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/M)\leq\theta\leq\pi /2. To calculate the pressures for this range of angles,the Rankine-Hugoniot equations are solved for pressure:
\frac(M^\sin^\theta -1)
To calculate the possible flow deflection angles, the relationship between shock angle \theta and \varphi is used:
\tan\varphi =2\cot\theta\frac\theta -1}.
Where \gamma is the ratio of specific heats and \varphi is the flow deflection angle.

抄文引用元・出典: フリー百科事典『 ウィキペディア(Wikipedia)
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