JNTU
JNTU B.Tech III CONCEPTUAL DESIGN OF FLIGHT VEHICLES Previous Question Paper (April - 2018 - R15)
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
What are the segments of air superiority mission profile?
Answer
The segments of an air superiority mission profile typically include: engine start and warm-up, taxi, takeoff, climb to cruise altitude, combat/loiter (including dash and maneuvering), return cruise, descent, and landing with appropriate fuel reserves.
How to find the takeoff weight of aircraft?
Answer
The takeoff weight is determined using the iterative weight estimation method based on the mission requirements. It is calculated by summing the empty weight, crew weight, payload weight, and fuel weight, where the fuel weight is derived from the fuel fractions of each mission segment using the Breuget Range Equation or mission segment analysis.
What is meant by Lofting?
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What is area rule in fuselage design?
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What is gear load factor?
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What are various types of aircraft subsystems?
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What is the effect of landing gear loads?
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What is meant by limit and ultimate loads?
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What is micro-burst?
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What is difference between sustained and instantaneous turn.
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PART - B
Explain briefly how wing tip shapes effect maximum lift coefficient?
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Write a short note on the requirements for designing a new aircraft.
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Explain about weight estimations for various type of aircraft from historical trends.
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Discuss briefly about effect of thrust to weight ratio, wing loading on aircraft performance.
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Explain about the Geometry sizing of fuselage, wing, tail and control surfaces.
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Explain design configuration for passenger compartment, cargo provisions, weapons carriage, gun installation.
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Write short note on:
- Engine cooling provisions
- Fuel system
- Stroke determination
- Gear load factor
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Explain in detail the factors for selection of propulsion system and engine integration with inlet geometry, location and type of nozzle.
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Discuss briefly about various aircraft loads and its classification.
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Explain the air load distribution on lifting surfaces.
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Explain how to maximize lift and drag coefficient with drag polar in subsonic and supersonic flows.
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Explain in detail about cooper-harper scale relation aircraft dynamic characteristics.
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Derive the relation for minimum thrust required for steady level flight.
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Define about Level turning flight, instantaneous turn rate, sustained turn rate and the factors effecting these turns.
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