It also contains an extensive set of formulae on oblique shock waves.

The external compression is caused by oblique shock waves inclined at an angle to the flow.

Oblique shock waves, strong and weak solutions.

If the compression fan is strong enough, another oblique shock wave will form, creating a second shock diamond.

The most common way to produce an oblique shock wave is to place a wedge into supersonic, compressible flow.

Discontinuous changes also occur in the pressure, density and temperature, which all rise downstream of the oblique shock wave.

Some supersonic intakes feature two or more ramps, operating in series, to generate multiple oblique shock waves.

An oblique shock wave, unlike a normal shock, is inclined with respect to the incident upstream flow direction.

Oblique shock waves are similar to normal shock waves, but they occur at angles less than 90 with the direction of flow.

Oblique shock waves are used predominantly in engineering applications when compared with normal shock waves.

A wedge located at the top wall of the combustion chamber was used to generate an oblique shock wave that impinges on the mixing layer.

Conical and oblique shock waves turn the flow, which continues in the new direction, until another flow disturbance is encountered downstream.

Spillage drag is high and pressure recovery low with only a plane shock wave in place of the normal set of oblique shock waves.

Compare oblique shock wave angles and Prandtl-Meyer expansion fan angles for the measured flow with perfect gas theory models.

At supersonic flight speeds, the deflection of the air stream creates an oblique shock wave at the forward end of the ramp.

Note: Comments made regarding 3 dimensional conical shock waves, generally also apply to 2D oblique shock waves.

A Mach wave is the weak limit of an oblique shock wave (a normal shock is the other limit).

NASA oblique shock wave calculator (Java applet).

While the upstream and downstream flow directions are unchanged across a normal shock, they are different for flow across an oblique shock wave.

As the Mach number of the upstream flow becomes increasingly hypersonic, the equations for the pressure, density, and temperature after the oblique shock wave reach a mathematical limit.

Ideally, the oblique shock wave should intercept the air intake lip, thus avoiding air spillage and pre-entry drag on the outer boundary of the deflected streamtube.

The key to reducing this drag is to use multiple small oblique shock waves, but this was difficult because the angle they make inside the intake changes with Mach number.

Then, a cone was put in a supersonic flow, the flow velocity was measured from the Mach angle of the oblique shock wave generating from the cone tip.

Similar to a normal shock wave, the oblique shock wave consists of a very thin region across which nearly discontinuous changes in the thermodynamic properties of a gas occur.

Conical (3-dimensional) and oblique shock waves (2D) are angled rearwards, like the bow wave on a ship or boat, and radiate from a flow disturbance such as a cone or a ramp.