GATE AE topic:compressible-flows PYQs & Answers — Page 4

Questions 31–40 of 41. Imported answers require independent review unless marked reviewed.

A supersonic flow in a constant area duct at Mach number

encounters a ramp of angle

(see Figure 1). The resulting oblique shock with shock angle

is then reflected from the top wall. For the reflected shock, the turn angle is

and the shock angle is

Diagram for Aerospace Engineering question 27

Use the weak shock solution from the

plot shown in Figure 2 to choose the correct option from the following.

Diagram for Aerospace Engineering question 27 (figure 2)

Your answerChoose one option.

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The static pressure ratio across a stationary normal shock is given by

where

is the upstream Mach number. For a stationary normal shock in air (

J/kg-K) with upstream flow conditions given by: speed 800 m/s, static temperature 300 K and static pressure 1 atm., the static pressure downstream of the shock is ______ atm. (round off to 2 decimal places).

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A thermocouple, mounted flush in an insulated flat surface in a supersonic laminar flow of air measures the

Your answerChoose one option.

static temperature.

temperature greater than static but less than total temperature.

total temperature.

temperature greater than total temperature.

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A shock wave is moving into still air in a shock tube. Which one of the following happens to the air?

Your answerChoose one option.

static temperature increases, total temperature remains constant.

static temperature increases, total temperature increases.

static temperature increases, total temperature decreases.

static pressure increases, total temperature remains constant.

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The relation between pressure (p) and velocity (V) for a steady, isentropic flow at two points along a streamline is, (c is a constant)

Your answerChoose one option.

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Air at 50 kPa pressure and 400 K temperature flows in a duct at Mach 3.0. A part of the flow leaks through an opening on the duct wall into the ambient, where the pressure is 30 kPa. The maximum Mach number achieved in the discharge is ______ (accurate to two decimal places). (Ratio of specific heats of air is

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Consider a 20° half-angle wedge in a supersonic flow at Mach 3.0 at standard sea-level conditions. If the shock-wave angle on the wedge is 36°, the Mach number of the tangential component of the flow post-shock is ______ (accurate to two decimal places).

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A De Laval nozzle is to be designed for an exit Mach number of 1.5. The reservoir conditions are given as

atm (gage),

. Assuming shock free flow in the nozzle, the exit absolute pressure (in atm) is __________ (in three decimal places)

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Consider a steady one dimensional flow of a perfect gas with heat transfer in a duct. The T-s diagram (shown below) shows both the static and the stagnation conditions at two locations, A and B, in the duct.

and

denote stagnation conditions for states A and B, respectively. It is known that

Diagram for Aerospace Engineering question 9

and

are the Mach numbers of the flow at locations A and B. Which of the following statements is true about the flow.

Your answerChoose one option.

Flow is subsonic and

Flow is supersonic and

Flow is subsonic and

Flow is supersonic and

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A trace from the schlieren photograph of the flow around a corner reveals the edges of the expansion fan as shown below. The leading and trailing edges of the expansion fan make the angles as shown. Assuming

, the angle of the expansion fan (in degrees) is _________ (in two decimal places)

Prandtl Meyer function is given by

Diagram for Aerospace Engineering question 34

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GATE AE topic:compressible-flows PYQs

Question 27

Question 37

Question 14

Question 15

Question 27

Question 45

Question 46

Question 8

Question 9

Question 34