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Engineering LibreTexts Given Two Angles, \(\delta\) and \(\theta\)

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  • It is sometimes useful to obtain a relationship where the two angles are known. The first upstream Mach number, \(M_1\) is

    Mach Number Angles Relationship

    {M_1}^2 = \dfrac{ 2 \,( \cot \theta + \tan \delta ) }
    { \sin 2 \theta - (\tan \delta)\, ( k + \cos 2 \theta) } \tag{59}

    The reduced pressure difference is
    \dfrac{2\,(P_2 - P_1) }{ \rho\, U^2} =
    \dfrac{2 \,\sin\theta \,\sin \delta }{ \cos(\theta - \delta)}
    \label{2Dgd:eq:OreducedPressure} \tag{60}
    The reduced density is
    \dfrac{\rho_ 2 -\rho_1 }{ \rho_2} =
    \dfrac{\sin \delta }{ \sin \theta\, \cos (\theta -\delta)}
    \label{2Dgd:eq:OreducedDensity} \tag{61}
    For a large upstream Mach number \(M_1\) and a small shock angle (yet not approaching zero), \(\theta\), the deflection angle, \(\delta\) must also be small as well. Equation (51) can be simplified into
    \theta \cong {k +1 \over 2} \delta
    \label{2Dgd:eq:OlargeM1theta} \tag{62}
    The results are consistent with the initial assumption which shows that it was an appropriate assumption.

    Fig. 12.9 Color-schlieren image of a two dimensional flow over a wedge. The total deflection angel (two sides) is \(20^\circ\) and upper and lower Mach angel are \(\sim 28^\circ\) and \(\sim 30^\circ\), respectively. The image show the end–effects as it has thick (not sharp transition) compare to shock over a cone. The image was taken by Dr.~Gary Settles at Gas Dynamics laboratory, Penn State University.


    • Dr. Genick Bar-Meir. Permission is granted to copy, distribute and/or modify this document under the terms of the GNU Free Documentation License, Version 1.2 or later or Potto license.