Atmosphere - Flight Mechanics & Space Dynamics - Aerospace Engineering Previous Year Questions

1

2008 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Atmosphere

Aerospace Engineering (AE) 2008

Which of the following statements is TRUE as the altitude increases in stratosphere of International Standard Atmosphere?

A

Temperature increases and dynamic viscosity decreases.

B

Temperature remains constant and pressure increases.

C

Temperature decreases and sound speed decreases.

D

Temperature remains constant and density decreases.

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2

2011 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Atmosphere

Aerospace Engineering (AE) 2011

The total temperature at point P is

A

806.37 K

B

1128.92 K

C

1612.74 K

D

2257.84 K

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3

2018 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Atmosphere

Aerospace Engineering (AE) 2018

Assuming ISA standard sea level conditions (288.16 K, density of 1.225 kg/m³, g = 9.81 m/s², R = 287 J/(kg·K)), the density (in kg/m³) of air at Leh, which is at an altitude of 3500 m above mean sea level is ________ (accurate to two decimal places).

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4

2019 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Atmosphere

Aerospace Engineering (AE) 2019

A cylindrical container of radius \(R = 50\) cm is filled with water up to a height \(h_0\). Upon rotating the cylinder about its central axis at a constant angular speed, the free surface takes a parabolic shape (see figure), and is displaced upwards by \(h_1 = 10\) cm at \(r = R\). The magnitude of the downward displacement \(h_2\) of the free surface at \(r = 0\) is __________ cm (round off to the nearest integer).

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5

2022 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Atmosphere

Aerospace Engineering (AE) 2022

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

A

The hydrostatic/ aerostatic equation is used

B

The temperature lapse rate is taken as $-10^{-2} \; K/m$

C

The sea level conditions are taken as: pressure, $p_s = 1.01325 \times 10^5 Pa$; temperature, $T_s = 300 \; K$; density, $\rho_s = 1.225 \; kg/m^3$

D

Air is treated as a perfect gas

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6

2023 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Atmosphere

Aerospace Engineering (AE) 2023

Which one of the following figures represents the qualitative variation of absolute deceleration \(\left|\frac{dV}{dt}\right|\) with altitude \(h\) (measured from the mean sea level) for a space vehicle undergoing a ballistic entry into the Earth’s atmosphere?

A

B

C

D

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7

2023 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Atmosphere

Aerospace Engineering (AE) 2023

Consider the International Standard Atmosphere (ISA) with \( h \) being the geopotential altitude (in km) and \( \frac{dT}{dh} \) being the temperature gradient (in K/m).
Which of the following combination(s) of \( \left( h, \frac{dT}{dh} \right) \) is/are as per ISA?

A

\((7, \; -6.5\times10^{-3}) \)

B

\((9, \; 4\times10^{-3}) \)

C

\((15, \; 0) \)

D

\((35, \; 3\times10^{-3}) \)

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8

2024 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Atmosphere

Aerospace Engineering (AE) 2024

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?

A

remains constant

B

increases linearly

C

decreases linearly

D

decreases exponentially

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