JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD B.Tech II FLIGHT MECHANICS I Previous Question Paper (December - 2017 - R13)
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.
Part A
(25 Marks)
What is Air data measurement? Explain briefly.
Answer
Air data measurement is the process of sensing and calculating critical flight parameters such as altitude, airspeed, Mach number, and angle of attack. It typically utilizes pitot-static systems to measure total and static pressures, which are then processed to determine the aircraft's state relative to the surrounding atmosphere.
Write a short note on FAA, ODM and WAT.
Answer
FAA (Federal Aviation Administration) is the national aviation authority of the United States, responsible for regulating civil aviation safety. ODM (Operating Data Manual) provides the performance data and operational limitations for a specific aircraft type. WAT (Weight, Altitude, Temperature) limits refer to the performance constraints where an aircraft's maximum allowable takeoff weight is reduced as altitude or ambient temperature increases, ensuring safe climb performance.
Explain the aircraft performance estimation in steady level flight.
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What differs the thrust producing and power producing engines?
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Give a short description on Instantaneous and sustained turns.
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Write the mathematical relation for specific excess power and explain its internal parameters.
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Write a note on environmental effects on aircraft performance.
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What do you mean by Baulked landing?
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Show the Payload-Range diagram with an example.
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How would you define the maximum take-off weight of an aircraft?
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Part B
(50 Marks)
Write a brief note on Drag reduction methods with neat schematic layouts.
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Discuss aircraft force system needed for formulating the performance equations of motion.
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An airscrew is required to produce a thrust of 4000N at a flight speed of 120 m/s at sea level. If the diameter is 2.5 m, estimate the minimum power which must be supplied based on Froude’s Momentum theory of Propulsion.
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For International Standard Atmosphere, explain variation of temperature, pressure variation with altitude with the help of neat diagram. Also define lapse rate, stratosphere and troposphere.
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In straight and level flight show that the velocity corresponding to minimum power required is 0.82 times the velocity corresponding to minimum thrust required.
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What is endurance of an airplane? Derive an expression to calculate endurance for propeller driven airplanes.
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Derive the Breguet Range formula for Jet-Propelled airplanes.
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Consider the Gulf stream-IV twin turbofan executive transport flying at an altitude of 30,000 ft, assuming a weight of 73,000 lb. Airplane data: Wing area= 950 ft2, Aspect ratio= 5.92, CDo = 0.015, and K = 0.08. Calculate: thrust required, minimum thrust required and the velocity at which it occurs. Assume Drag Polar, CD = 0.015 + 0.08 CL2.
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Describe the equations of motion of an aircraft undergoing lateral maneuver or level turn and derive an expression for radius of turn. Discuss with the help of a diagram the maneuver boundaries for turning performance.
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Derive an expression for maximum rate of climb and angle of attack for propeller driven airplane.
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What is the role of Ceiling in aircraft performance? Explain the terms Absolute Ceiling and Service Ceiling?
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An airplane accelerates from rest to a velocity VTo. Show with a diagram all the forces acting in the process till the airplane is airborne. Hence develop an expression for the take-off run and the time to cover the above take off run.
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How wind, weight, runway will effect on take-off distances? What measures can be adopted to optimize the performance?
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Write a short note on the following terms related to fuel planning: (i) Fuel tinkering (ii) Fuel reserve.
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Explain the following method of corrections in performance measurements: (a) Weight and Temperature Corrections (b) Runway Corrections.
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Estimate the maximum take-off weight for an Anti submarine warfare aircraft with simple mission profile, High bypass turbofan engine, Mach 0.6, Range = 1500 Nautical miles, Endurance = 3hrs, (L/D)max = 16, Payload weight = 10,000 pounds, Crew weight = 800 pounds at a height of 30,000 feet. Assume the required historical trends.
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