Airplane performance - Flight Mechanics & Space Dynamics - Aerospace Engineering Previous Year Questions

1

2007 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2007

Let an airplane in a steady level flight be trimmed at a certain speed. A level and steady flight at a higher speed could be achieved by changing

A

engine throttle only

B

elevator only

C

throttle and elevator together

D

rudder only

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2

2007 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2007

A piston-prop airplane having propeller efficiency, η_p = 0.8 and weighing 73108 N could achieve maximum climb rate of 15 m/s at flight speed of 50 m/s. The excess Brake Power (BP) at the above flight condition will be

A

1700 kW

B

2100 kW

C

1371 kW

D

6125 kW

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3

2007 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2007

The maximum rate of climb achievable by this airplane at 5 km altitude will be

A

1.65 m/s

B

0.51 m/s

C

1.43 m/s

D

3.65 m/s

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4

2008 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2008

The service ceiling of a transport aircraft is defined as the altitude

A

that is halfway between sea-level and absolute ceiling

B

at which it can cruise with one engine operational

C

at which its maximum rate of climb is zero

D

at which its maximum rate of climb is 0.508 m/s

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5

2008 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2008

The drag of an aircraft in steady climbing flight at a given forward speed is

A

inversely proportional to climb angle

B

higher than drag in steady level flight at the same forward speed

C

lower than drag in steady level flight at the same forward speed

D

independent of climb angle

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6

2008 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2008

The parameters that remain constant in a cruise-climb of an aircraft are

A

equivalent airspeed and lift coefficient

B

altitude and lift coefficient

C

equivalent airspeed and altitude

D

lift coefficient and aircraft mass

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7

2008 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2008

An aircraft is cruising at a true air speed (TAS) of 100 m/s under ISA conditions, at an altitude at which the density of free stream is 0.526 kg/m³. What will be the equivalent air speed (EAS)?

A

65.5 m/s

B

72.5 m/s

C

110.5 m/s

D

152.7 m/s

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8

2008 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2008

To maximize range of a jet engine aircraft, it should be flown at a velocity that maximizes

A

\(C_L/C_D\)

B

\(C_L^{0.5}/C_D\)

C

\(C_L^{1.5}/C_D\)

D

\(C_L^2/C_D\)

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9

2009 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2009

An aircraft of mass 2500 kg in straight and level flight at a constant speed of 100 m/s has available excess power of \(1.0 \times 10^6\) W. The steady rate of climb it can attain at that speed is

A

100 m/s

B

60 m/s

C

40 m/s

D

20 m/s

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10

2016 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2016

The pitch angle and the angle of attack for a fixed wing aircraft are equal during

A

wings level constant altitude flight.

B

unaccelerated climb.

C

unaccelerated descent.

D

landing.

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11

2016 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2016

The load factor of an aircraft turning at a constant altitude is 2. The coefficient of lift required for turning flight as compared to level flight at the same speed will be

A

same

B

half

C

double

D

four times

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12

2016 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2016

An aircraft weighing 10000 N is flying level at 100 m/s and it is powered by a jet engine. The thrust required for level flight is 1000 N. The maximum possible thrust produced by the jet engine is 5000 N. The minimum time required to climb 1000 m, when flight speed is 100 m/s, is ______ s.

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13

2016 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2016

The aircraft velocity (m/s) components in body axes are given as [u, v, w] = [100, 10, 10]. The air velocity (m/s), angle of attack (deg) and sideslip angle (deg) in that order are

A

[120, 0.1, 0.1]

B

[100, 0.1, 0.1]

C

[100.995, 0.1, 5.73]

D

[100.995, 5.71, 5.68]

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14

2017 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2017

An aircraft landing gear can be idealized as a single degree of freedom spring-mass-damper system. The desirable damping characteristics of such a system is:

A

Under damped

B

Over damped

C

Critically damped

D

Undamped

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15

2017 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2017

A pilot was flying a single engine propeller aircraft and maintaining a steady level flight at a lift coefficient, \(C_L=0.5\) at an altitude of 500 m. Due to some emergency, at the same altitude (500 m), the pilot had to fully deploy the landing gear. If the pilot wants to maintain steady level flight at the same \(C_L=0.5\) and at the same altitude, which of the following control actions should the pilot undertake:

A

move the elevator up, and decrease the throttle

B

move the elevator up, and increase the throttle

C

move the elevator down, and decrease the throttle

D

move the elevator down, and increase the throttle

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16

2017 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2017

An aircraft is to be designed to ensure that it has enough excess power to achieve steady climb at flight path angle, \(\gamma=10\) degrees, maintaining \(\frac{C_L}{C_D} = 10.0\). The numerical value of the thrust to weight ratio of the complete aircraft to meet the above requirement under standard atmospheric condition will be __________ (in three decimal place).

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17

2018 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2018

A jet aircraft is initially flying steady and level at its maximum endurance condition. For the aircraft to fly steady and level, but faster at the same altitude, the pilot should

A

increase thrust alone.

B

increase thrust and increase angle of attack.

C

increase thrust and reduce angle of attack.

D

reduce angle of attack alone.

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18

2018 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2018

An airplane requires a longer ground roll to lift-off on hot summer days because

A

the thrust is directly proportional to free-stream density.

B

the thrust is directly proportional to weight of the aircraft.

C

the lift-off distance is directly proportional to free-stream density.

D

the runway friction is high on hot summer days.

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19

2018 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2018

The highest limit load factor experienced by a civil transport aircraft is in the range

A

0.0 – 2.0

B

2.0 – 5.0

C

5.0 – 8.0

D

8.0 – 10.0

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20

2018 · Aerospace Engineering · Flight Mechanics & Space Dynamics · Airplane performance

Aerospace Engineering (AE) 2018

An aircraft with mass of 400,000 kg cruises at 240 m/s at an altitude of 10 km. Its lift to drag ratio at cruise is 15. Assuming g as 9.81 m/s², the power (in MW) needed for it to cruise is ________ (accurate to two decimal places).

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