Oblique shock wave calculator
From the continuity equation of a compressible flow we can derive a
relationship between the angle of an oblique shock wave and the angle of
a 'wedge' encountering a supersonic flow. It is also possible to
determine the Mach speed of the flow downstream the shockwave. Fluid
flows are classified as follow:
- Subsonic flows: M<0.8 flows with Mach number less than 0.8
- Transonic flows: 0.8<M<1.4, a flow that is transitioning from
subsonic velocity to sonic or supersonic.
- Supersonic flows: 1.4<M<5, flows encountered in jet fighters and
- Hypersonic flows: M>5, atmospheric space re-entry capsule is a
shockwaves are characterised with an abrupt change in pressure within
a small area in which a burst of energy propagates through a fluid
medium. Furthermore, shockwaves are observable at a certain angle
engulfing the supersonic object travelling through a gaseous or liquid
The application in the next section has 2 sets of fields, the ones in blue are result outputs and the ones in black are your input entries. All you need to enter is the incoming flow Mach number, the angle of the wedge and the heat capacity ratio. The image above shows the inputs and outputs of the calculator.