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Compressible flow
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===Supersonic aircraft inlets=== Perhaps the most common requirement for oblique shocks is in supersonic aircraft inlets for speeds greater than about Mach 2 (the F-16 has a maximum speed of Mach 2 but doesn't need an oblique shock intake). One purpose of the inlet is to minimize losses across the shocks as the incoming supersonic air slows down to subsonic before it enters the turbojet engine. This is accomplished with one or more oblique shocks followed by a very weak normal shock, with an upstream Mach number usually less than 1.4. The airflow through the intake has to be managed correctly over a wide speed range from zero to its maximum supersonic speed. This is done by varying the position of the intake surfaces. Although variable geometry is required to achieve acceptable performance from take-off to speeds exceeding Mach 2 there is no one method to achieve it. For example, for a maximum speed of about Mach 3, the [[XB-70]] used rectangular inlets with adjustable ramps and the [[SR-71]] used circular inlets with adjustable [[inlet cone]]. {|style="margin: 0 auto;" |[[File:North American XB-70 above runway ECN-792.jpg|thumb|left|XB-70 rectangular inlets with ramps (not visible)]] |[[File:Lockheed SR-71 Blackbird.jpg|thumb|SR-71 round inlets with inlet cones]] |}
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