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  2. Oblique shock - Wikipedia

    en.wikipedia.org/wiki/Oblique_shock

    An oblique shock wave is a shock wave that, unlike a normal shock, ... NASA oblique shock wave calculator Archived 2011-07-18 at the Wayback Machine (Java applet)

  3. Shock polar - Wikipedia

    en.wikipedia.org/wiki/Shock_polar

    Shock polar in the pressure ratio-flow deflection angle plane for a Mach number of 1.8 and a specific heat ratio 1.4. The minimum angle, , which an oblique shock can have is the Mach angle = ⁡ (/), where is the initial Mach number before the shock and the greatest angle corresponds to a normal shock.

  4. Mach wave - Wikipedia

    en.wikipedia.org/wiki/Mach_wave

    A Mach wave is the weak limit of an oblique shock wave where time averages of flow quantities don't change (a normal shock is the other limit). If the size of the object moving at the speed of sound is near 0, then this domain of influence of the wave is called a Mach cone. [3] [4]

  5. Normal shock tables - Wikipedia

    en.wikipedia.org/wiki/Normal_shock_tables

    In aerodynamics, the normal shock tables are a series of tabulated data listing the various properties before and after the occurrence of a normal shock wave. [1] With a given upstream Mach number , the post-shock Mach number can be calculated along with the pressure , density , temperature , and stagnation pressure ratios.

  6. Rankine–Hugoniot conditions - Wikipedia

    en.wikipedia.org/wiki/Rankine–Hugoniot_conditions

    A schematic diagram of a shock wave situation with the density , velocity , and temperature indicated for each region.. The Rankine–Hugoniot conditions, also referred to as Rankine–Hugoniot jump conditions or Rankine–Hugoniot relations, describe the relationship between the states on both sides of a shock wave or a combustion wave (deflagration or detonation) in a one-dimensional flow in ...

  7. Swept wing - Wikipedia

    en.wikipedia.org/wiki/Swept_wing

    Now, even if the local speed of the air on the upper surface of the wing becomes supersonic, a shock wave cannot form there because it would have to be a sweptback shock – swept at the same angle as the wing – i.e., it would be an oblique shock. Such an oblique shock cannot form until the velocity component normal to it becomes supersonic ...

  8. Shocks and discontinuities (magnetohydrodynamics) - Wikipedia

    en.wikipedia.org/wiki/Shocks_and_discontinuities...

    In magnetohydrodynamics (MHD), shocks and discontinuities are transition layers where properties of a plasma change from one equilibrium state to another. The relation between the plasma properties on both sides of a shock or a discontinuity can be obtained from the conservative form of the MHD equations, assuming conservation of mass, momentum, energy and of .

  9. Shock wave - Wikipedia

    en.wikipedia.org/wiki/Shock_wave

    In this case the gas ahead of the shock is supersonic (in the laboratory frame), and the gas behind the shock system is either supersonic (oblique shocks) or subsonic (a normal shock) (Although for some oblique shocks very close to the deflection angle limit, the downstream Mach number is subsonic.) The shock is the result of the deceleration ...