Consider supersonic airflow approaching the nose of a...

Name: Problem 89, Chapter 17: Thermodynamics: An Engineering Approach w/ Student Resources DVD
Uploaded: 2020-07-08T04:41:19-08:00
Duration: 17 s
Channel: Dading Chen
Description: Consider supersonic airflow approaching the nose of a two-dimensional wedge at a Mach number of 5. Using Fig. 17-41, determine the minimum shock angle and the maximum deflection angle a straight oblique shock can have.

Consider supersonic airflow approaching the nose of a two-dimensional wedge at a Mach number of 5. Using Fig. 17-41, determine the minimum shock angle and the maximum deflection angle a straight oblique shock can have.

Key Concepts

Supersonic Mach Number

The Mach number is the ratio of the flow speed to the local speed of sound, and in supersonic flows (Mach number greater than 1), compressibility effects become significant. The Mach number is a crucial parameter in determining the behavior and characteristics of shock waves, including their angles and the associated flow deflections.

Deflection Angle

The deflection angle represents the amount by which the supersonic flow is turned as it passes through the shock. There is a maximum deflection angle possible for a given flow Mach number and shock configuration, beyond which the shock can no longer remain attached to the body, leading to a detached shock scenario.

Oblique Shock Waves

Oblique shock waves are discontinuities that develop in supersonic flows when the flow is turned by a compression surface, such as a wedge. Their properties are governed by the relationship between the incoming Mach number, the shock angle, and the flow deflection angle, and they influence the pressure, temperature, and density of the flow behind the shock.

Shock Angle

The shock angle is the angle between the free-stream flow direction and the shock wave itself. It is a fundamental parameter in the analysis of oblique shocks; a minimum shock angle corresponds to the condition where the shock is just strong enough to deflect the flow by a prescribed angle, defining the weakest possible shock in that scenario.

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