Aerospace Engineering > GATE 2018 > Compressible Flow
Consider a 20° half-angle wedge in a supersonic flow at Mach 3.0 at standard sea-level conditions. If the shock-wave angle on the wedge is 36°, the Mach number of the tangential component of the flow post-shock is ________ (accurate to two decimal places).
Correct : 1.90 to 2.20
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