Normal and Oblique Shock Waves Questions and Answers

Assertion (A): A shock wave is an isentropic process.

Reason (R): No heat is transferred to or from the gas as it crosses the shock.

Select the correct answer from the options below.

Assertion (A): Regular reflection of an oblique shock from a wall fails at high incident shock angles.

Reason (R): The reflected shock has to turn a stream already slowed by the incident shock.

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Assertion (A): An oblique shock at a given upstream Mach number destroys less stagnation pressure than a normal shock does.

Reason (R): Only the velocity component normal to an oblique shock is processed by it.

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Consider the following statements about a normal shock wave:

1. The upstream flow is supersonic and the downstream flow subsonic.

2. Static pressure, temperature and density all rise across it.

3. Stagnation pressure rises across it.

Which of the statements given above is or are correct?

Consider the following statements about an oblique shock wave:

1. The velocity component tangential to the shock is unchanged.

2. The component normal to the shock behaves as it would through a normal shock.

3. The flow is deflected away from the shock surface.

Which of the statements given above is or are correct?

Consider the following statements about the theta-beta-Mach relation:

1. For deflections below the maximum it gives two solutions.

2. The weak solution is the one usually observed.

3. The strong solution always leaves the flow supersonic.

Which of the statements given above is or are correct?

Consider the following statements about a detached bow shock:

1. It forms when the required deflection exceeds the maximum for the free-stream Mach number.

2. It is effectively a normal shock at the stagnation streamline.

3. It becomes stronger with increasing distance from the body.

Which of the statements given above is or are correct?

Consider the following statements about the limits of normal shock behaviour in air:

1. The density ratio approaches six as the upstream Mach number grows without bound.

2. The downstream Mach number approaches about 0.378 in the same limit.

3. The static pressure ratio approaches a finite limit of about 45.

Which of the statements given above is or are correct?

Consider the following statements about shock reflection from a plane wall:

1. The reflected wave restores the flow to a direction parallel to the wall.

2. The reflected shock is not at the same angle as the incident shock.

3. The reflected wave is an expansion fan rather than a shock.

Which of the statements given above is or are correct?

Consider the following statements about supersonic intake design:

1. Several weak oblique shocks recover more stagnation pressure than one strong normal shock.

2. Stagnation temperature is unaffected by the shock system.

3. The shock system can be arranged to produce no entropy rise at all.

Which of the statements given above is or are correct?