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JNTU B.Tech II FLIGHT MECHANICS I Previous Question Paper (December - 2018 - R13)

B.Tech | II | II-II | R13 | December - 2018

Answer PaperPaper Code: 114BHMaximum Marks: 75Time: 3 Hours

Note: This question paper contains two parts A and B. Part A is compulsory which carries 25 marks. Answer all questions in Part A. Part B consists of 5 Units. Answer any one full question from each unit. Each question carries 10 marks and may have a, b, c as sub questions.

Part A

(25 Marks)

125 marks
a
Mention types of thrust producing engines.
2 marks

Answer

Thrust producing engines are broadly classified into: 1) Air-breathing engines (Turbojet, Turbofan, Turboprop, Ramjet, and Pulsejet) and 2) Non-air-breathing engines (Rocket engines).

b
Discuss the thrust variation with speed of aircraft fitted with propeller engine.
3 marks

Answer

For a propeller-driven aircraft, thrust is generated by accelerating a mass of air. Since power output remains relatively constant over a range of speeds, thrust is inversely proportional to the flight velocity (T = P/V). Consequently, as the aircraft speed increases, the available thrust decreases significantly.

c
What do you understand by word performance of aircraft?
2 marks

Answer

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d
How optimum cruise speed for an aircraft is decided?
3 marks

Answer

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e
Explain the following: i) Specific thrust ii) Thrust specific fuel consumption.
2 marks

Answer

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f
Discuss different types of aircraft ceilings.
3 marks

Answer

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g
What is baulked landing?
2 marks

Answer

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h
How ground influences Takeoff and Landing?
3 marks

Answer

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i
What corrections are adopted for collected date of weight and temperature?
2 marks

Answer

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j
How route analysis is carried out? Explain.
3 marks

Answer

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Part B

(50 Marks)

210 marks
a
Enumerate the effects of altitude on the following: i) Thrust produced ii) propulsive power iii) Specific fuel consumption.
5 marks

Answer

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b
The thrust of a jet engine decreases as flight velocity increases. Maximum thrust at zero velocity at sea level is 250 kN. Calculate the thrust at an altitude of 3km at Mach 0.7.
5 marks

Answer

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OR
310 marks
a
What is drag polar? From first principles, show that velocity for level flight is function of thrust loading, wing loading and drag polar.
5 marks

Answer

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b
An airfoil with chord of 1.5m length is inclined an angle of 4 degree with free stream. If flow velocity is 38 m/s at standard sea level, calculate the total drag per unit span. Take viscosity coefficient at sea level, 1.7894 × 10⁻⁵ kg/m.s.
5 marks

Answer

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410 marks
a
Describe the following for Jet and Propeller engines: i) Thrust required and thrust available ii) Power required and power available
5 marks

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b
A twin turbo fan aircraft weighing 380kN is moving at a speed of 150m/s at an altitude of 12 km above sea level. Calculate the thrust required. Take plan form area 90m², aspect ratio 5.92, zero lift drag coeff. 0.014, K=0.09.
5 marks

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OR
510 marks
a
An airplane propelled by propeller engine in on cruise phase of flight. Explain on how to optimum cruising performance.
5 marks

Answer

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b
Calculate lift to drag ratio for an airplane of 420kN weight, cruising at a speed of 200m/s, and has S = 4.5, CD,0 = 0.013, K = 0.075.
5 marks

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610 marks
a
Bring out any five differences between glide and powered decent.
5 marks

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b
Calculate the max range an aircraft can cruise at an altitude of 15km, if its usable fuel weight is 130kN. The thrust specific fuel consumed is 0.65 N per hour per Newton thrust.
5 marks

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OR
710 marks
a
An aircraft propelled by jet engine is set to climb to desired altitude. Discuss how to optimize the climb with regard to climb angle and rate of climb.
5 marks

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b
Calculate minimum velocity an airplane can cruise at desired altitude with the following date. Wing loading 4000 N/m², thrust to weight 0.4, CD,0 = 0.012, K = 0.08, density 0.98 kg/m³.
5 marks

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8
Explain different types of velocities experienced by an airplane initiated with takeoff phase on runway, until it clears obstacle height (use figures, charts, equations to support justification).
10 marks

Answer

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OR
910 marks
a
Briefly, discuss on how landing phase is critical.
5 marks

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b
Calculate approach and flare distances of an airplane weighing 400kN landing at standard sea level. Take friction coefficient 0.38 and a approach angle 3.5 degrees.
5 marks

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10
Explain in detail the following: a) Route analysis and optimization b) Payload and range interdependency.
10 marks

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OR
11
Enumerate on the following: a) Parametric data analysis b) Maximum takeoff weight determination.
10 marks

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About this paper

This page contains the question paper of FLIGHT MECHANICS I from JNTU for B.Tech AE II II-II, December - 2018, R13.

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