GATE AE Atmosphere PYQs & Answers

Questions 1–10 of 14. Imported answers require independent review unless marked reviewed.

A general aviation airplane is flying at an altitude of 5000 m. The indicated airspeed is 250 km/h. Assume that there are no instrument errors and position errors. Neglecting compressibility effects, which one of the following options is FALSE?

Your answerChoose one option.

The true airspeed is greater than 250 km/h.

The calibrated airspeed is 250 km/h.

The true airspeed is 250 km/h.

The equivalent airspeed is 250 km/h.

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On Day 1, an aircraft flies with a speed of V₁ m/s at an altitude where the temperature is T₁ K. On Day 2, the same aircraft flies with a speed √1.2 V₁ m/s at an altitude where the temperature is 1.2 T₁ K. How does the Mach number M₂ on Day 2 compare with the Mach number M₁ on Day 1?

Assume ideal gas behavior for air. Also assume the ratio of specific heats and molecular weight of air to be the same on both the days.

Your answerChoose one option.

M₂ = 0.6 M₁

M₂ = M₁

M₂ =

M₁

M₂ = √1.2 M₁

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As per the International Standard Atmosphere model, which one of the following options about density variation with increase in altitude in the isothermal layer is correct?

Your answerChoose one option.

remains constant

increases linearly

decreases linearly

decreases exponentially

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For an aircraft moving at 4 km altitude above mean sea level at a Mach number of 0.2, the ratio of equivalent air speed to true air speed is ________ (rounded off to 2 decimal places).

The density of air at mean sea level is 1.225 kg/m

and at 4 km altitude is 0.819 kg/m

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Which one of the following figures represents the qualitative variation of absolute deceleration

with altitude

(measured from the mean sea level) for a space vehicle undergoing a ballistic entry into the Earth’s atmosphere?

Your answerChoose one option.

Diagram for Aerospace Engineering question 24

Diagram for Aerospace Engineering question 24 (figure 2)

Diagram for Aerospace Engineering question 24 (figure 3)

Diagram for Aerospace Engineering question 24 (figure 4)

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Airplane A and Airplane B are cruising at altitudes of 2 km and 4 km, respectively. The free stream density and static pressure at altitude 2 km are 1.01 kg/m

and 79.50 kPa, respectively, and at altitude 4 km, they are 0.82 kg/m

and 61.70 kPa, respectively. The differential pressure reading from the pitot-static tubes is 3 kPa for both the airplanes. Assuming incompressible flow, the ratio of cruise speeds of Airplane A to Airplane B is _____. (round off to two decimal places)

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Consider the International Standard Atmosphere (ISA) with

being the geopotential altitude (in km) and

being the temperature gradient (in K/m). Which of the following combination(s) of

is/are as per ISA?

Your answerSelect all correct options. You can choose more than one.

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For International Standard Atmosphere (ISA) up to 11 km, which of the following statement(s) is/are true?

Your answerSelect all correct options. You can choose more than one.

The hydrostatic/ aerostatic equation is used

The temperature lapse rate is taken as

The sea level conditions are taken as: pressure,

; temperature,

; density,

Air is treated as a perfect gas

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For a conventional airplane in straight, level, constant velocity flight condition, which of the following condition(s) is/are possible on Euler angles (φ, θ, ψ), angle of attack (α) and the sideslip angle (β)?

Your answerSelect all correct options. You can choose more than one.

φ = 0°, θ = 2°, ψ = 0°, α = 2°, β = 0°

φ = 5°, θ = 0°, ψ = 0°, α = 2°, β = 0°

φ = 0°, θ = 3°, ψ = 0°, α = 3°, β = 5°

φ = 0°, θ = 5°, ψ = 0°, α = 2°, β = 5°

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Let

be the true airspeed of an aircraft flying at a certain altitude where the density of air is

, and

be the equivalent airspeed. If

is the density of air at sea-level, what is the ratio

equal to?

Your answerChoose one option.

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GATE AE Atmosphere PYQs

How to practice Atmosphere

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Question 61

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Question 27

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Question 12