GATE AE 2024 Paper 1 — page 7

Questions 19–21 of 65. Imported answers require review unless explicitly marked reviewed.

In an airbreathing gas turbine engine, the combustor inlet temperature is 600 K. The heating value of the fuel is 43.4 × 10⁶ J/kg. Assume Cₚ to be 1100 J/kg K for air and burned gases, and fuel-air ratio f<< 1.0. Neglect kinetic energy at the inlet and exit of the combustor and assume 100% burner efficiency. What is the fuel-air ratio required to achieve 1300 K temperature at the combustor exit?

Your answerChoose one option.

0.0177

0.0215

0.0127

0.0277

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Which one of the following figures represents the drag polar of a general aviation aircraft?

Your answerChoose one option.

Diagram for Aerospace Engineering question 20

Diagram for Aerospace Engineering question 20 (figure 2)

Diagram for Aerospace Engineering question 20 (figure 3)

Diagram for Aerospace Engineering question 20 (figure 4)

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In the context of steady, inviscid, incompressible flows, consider the superposition of a uniform flow with speed U along the positive x-axis (from left to right), and a source of strength Λ located at the origin. Which one of the following statements is NOT true regarding the location of the station point of the resulting flow?

Your answerChoose one option.

It is located to the left of the origin

It moves closer to the origin for increasing Λ, while U is held constant

It moves closer to the origin for increasing U, while Λ is held constant

It is located along the x-axis

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2024 · Paper 1

Question 19

Question 20

Question 21