# oblique shock

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## oblique shock

[ə′blēk ′shäk]
(fluid mechanics)
McGraw-Hill Dictionary of Scientific & Technical Terms, 6E, Copyright © 2003 by The McGraw-Hill Companies, Inc.

## inclined shock

When ball is in the center, it means that the aircraft is level. If the aircraft is inclined to either side, the ball will be not be in the center anymore.
A shock wave that forms on a sharp-pointed object moving through the air at a speed greater than the speed of sound. Air passing through an inclined shock wave is slowed down, but if the wave angle is less than about 70° it still will be supersonic. The area bounded by the sides of an oblique shock wave forms the Mach cone. Also known as an oblique shock.

## oblique shock wave

A shock wave that forms on a sharp-pointed object moving through the air at a speed greater than the speed of sound. Air passing through an oblique shock wave is slowed down but if the wave angle is less than about 70°, it still will be supersonic. The area bounded by the sides of an oblique shock wave forms the Mach cone. Also known as an oblique shock. See also Mach cone.
An Illustrated Dictionary of Aviation Copyright © 2005 by The McGraw-Hill Companies, Inc. All rights reserved
References in periodicals archive ?
The 14-X B model lower surface was designed based on the two-dimensional compressible flow (oblique shock wave relationships) and expansion wave (Prandtl-Meyer theory), considering the simplest case, that is, no viscous flow, calorically perfect air ([gamma] = 1.4), and scramjet engine with power off [11].
The static pressure measurements at the lower surface of the 14-X B model are compared with the static pressure evaluated at the same freestream conditions via no viscous flow, calorically perfect air ([gamma] = 1.4) oblique shock wave relationships, and computational fluid dynamics (CFD) simulations using the ANSYS FLUENT software (Figure 9).
Oblique shock waves, expansion waves and shock wave interactions are mainly considered.
The compression ramp is designed to create a series of oblique shock waves.
In a 26-inch fully retracted aft position, at the design cruise Mach number of 3.2, an oblique shock system exists with the lead shock stretched between the cone's apex and the nacelle lip, to yield a maximum total pressure recovery of 40:1.
Readers should have background in basic shock wave concepts, including the equations for an oblique shock in a steady flow of a perfect gas.
Subsequent chapters address steady one-dimensional flow, normal shock waves, oblique shock and expansion waves, compressible flow equations, similarity rule, and two-dimensional compressible flows, among other topics, ending with chapters on ramjet, and jets.
If the exit pressure is slightly less than the back pressure, then oblique shock waves occur at the nozzle exit as shown in figure 2.
Oblique Shock waves and normal shocks are very small regions in the gas where the gas properties change by a large amount.
It can be seen from Figure 4(a) that an obvious oblique shock formed at the first fuel injection orifice, and then it was followed by a long shock train.
Among the titles are the periodic and quasi-periodic motion of point vortices, vortices in superconductors, vortex dipole coordinates on spheres, the interaction between longitudinal vortices and normal and oblique shocks, and typical vortex phenomena in flow fields past space vehicles.

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