GATE AE 2019 Paper 1 — page 13

Questions 37–39 of 65. Imported answers require review unless explicitly 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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Which of the following statements about adverse yaw of an airplane is/are correct? P. It is caused by flow separation resulting from large rudder deflection. Q. It is caused by dissimilar drag forces acting on the two halves of the wing resulting from aileron deflections of same magnitude. R. It can be eliminated by ensuring that the upward deflection of one aileron is greater than the downward deflection of the opposite aileron.

Your answerChoose one option.

P only

Q only

P and R

Q and R

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In a turbot engine, the compressor outlet temperature increases with decrease efficiency of the compressor. If the turbine inlet temperature remains constant, with decreasing efficiency of the compressor, the thrust specific fuel consumption of the engine

Your answerChoose one option.

decreases, as the heat input is lower.

remains unchanged.

increases, as the compressor needs more work input from the turbine.

decreases, as the thrust produced is higher.

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2019 · Paper 1

Question 27

Question 28

Question 29