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  2. Inlet cone - Wikipedia

    en.wikipedia.org/wiki/Inlet_cone

    An inlet cone, as part of an Oswatitsch-type inlet used on a supersonic aircraft or missile, is the 3D-surface on which supersonic ram compression for a gas turbine engine or ramjet combustor takes place through oblique shock waves. Slowing the air to low supersonic speeds using a cone minimizes loss in total pressure (increases pressure recovery).

  3. Lockheed Martin X-59 Quesst - Wikipedia

    en.wikipedia.org/wiki/Lockheed_Martin_X-59_QueSST

    The Lockheed Martin X-59 Quesst ("Quiet SuperSonic Technology"), sometimes styled QueSST, is an American experimental supersonic aircraft under development by Skunk Works for NASA's Low-Boom Flight Demonstrator project. [2] Preliminary design started in February 2016, with the X-59 planned to begin flight testing in 2021.

  4. Shock wave - Wikipedia

    en.wikipedia.org/wiki/Shock_wave

    In this case, the gas ahead of the shock is stationary (in the laboratory frame) and the gas behind the shock can be supersonic in the laboratory frame. The shock propagates with a wavefront which is normal (at right angles) to the direction of flow. The speed of the shock is a function of the original pressure ratio between the two bodies of gas.

  5. Swept wing - Wikipedia

    en.wikipedia.org/wiki/Swept_wing

    Swept wings on supersonic aircraft usually lie within the cone-shaped shock wave produced at the nose of the aircraft so they will "see" subsonic airflow and work as subsonic wings. The angle needed to lie behind the cone increases with increasing speed, at Mach 1.3 the angle is about 45 degrees, at Mach 2.0 it is 60 degrees. [10]

  6. Drag-reducing aerospike - Wikipedia

    en.wikipedia.org/wiki/Drag-reducing_aerospike

    A drag-reducing aerospike is a device (see nose cone design) used to reduce the forebody pressure aerodynamic drag of blunt bodies at supersonic speeds. The aerospike creates a detached shock ahead of the body. Between the shock and the forebody a zone of recirculating flow occurs which acts like a more streamlined forebody profile, reducing ...

  7. North American XB-70 Valkyrie - Wikipedia

    en.wikipedia.org/wiki/North_American_XB-70_Valkyrie

    The XB-70 was designed to use supersonic technologies developed for the Mach 3 SM-64 Navaho, as well as a modified form of the Navaho's inertial guidance system. [ 76 ] The XB-70 used compression lift , which resulted from a shock wave generated by the leading edge of the engine intake splitter below the apex of the wing. [ 77 ]

  8. Rolls-Royce/Snecma Olympus 593 - Wikipedia

    en.wikipedia.org/wiki/Rolls-Royce/Snecma_Olympus_593

    The Rolls-Royce/Snecma Olympus 593 was an Anglo-French turbojet with reheat, which powered the supersonic airliner Concorde.It was initially a joint project between Bristol Siddeley Engines Limited (BSEL) and Snecma, derived from the Bristol Siddeley Olympus 22R engine.

  9. Hypersonic speed - Wikipedia

    en.wikipedia.org/wiki/Hypersonic_speed

    Simulation of hypersonic speed (Mach 5) While the definition of hypersonic flow can be quite vague and is generally debatable (especially due to the absence of discontinuity between supersonic and hypersonic flows), a hypersonic flow may be characterized by certain physical phenomena that can no longer be analytically discounted as in supersonic flow.

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