JNTU
JNTU B.Tech II AIRCRAFT PERFORMANCE Previous Question Paper (May - 2019 - R16)
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
Define the aircraft mission profile.
Answer
An aircraft mission profile is a graphical or tabular representation of the various phases of a flight, such as taxi, take-off, climb, cruise, loiter, descent, and landing, illustrating the sequence of operations and the corresponding fuel consumption or distance covered for each segment.
Differentiate between standard and off-standard atmosphere.
Answer
A Standard Atmosphere is a theoretical model (like ISA) that defines atmospheric properties such as pressure, temperature, and density as a function of altitude based on fixed sea-level conditions. An Off-Standard Atmosphere refers to any real-world atmospheric state where the actual temperature or pressure deviates from these standard values, significantly impacting aircraft performance calculations.
Distinguish between Infinite and Finite wings.
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What is the effect of Reynolds number on skin friction drag?
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What do you mean by drag divergence number?
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Explain the terms absolute ceiling and service ceiling.
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Write a short note on maneuver boundaries.
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Define Instantaneous and sustained turns.
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Explain briefly about Baulked Landing.
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What do you know about discontinued landing?
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Part B
Define the terms indicated airspeed, calibrated airspeed, equivalent airspeed and true airspeed as used in the calibration of airspeed indicator.
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Discuss the following terms related to aircraft performance: i) Scheduled performance and ii) Operational performance.
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What is International standard atmosphere? Explain the variation of temperature with altitude in standard model of atmosphere
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Calculate the value of pressure, pressure ratio, density, density ratio and temperature for the standard atmosphere at an altitude of 6500 m. The standard SL values are Pressure = 1 atm, density = 1.2256 kg/m3, temperature 288 K and lapse rate = - 0.0065 K/m.
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Explain role of (CL)max on stalling velocity. Justify your answer with suitable mathematical derivation and diagram.
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Define pressure coefficient and derive the relation to obtain lift coefficient from Cp.
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Illustrate the variation of power, thrust and specific fuel consumption with velocity and altitude for an aircraft with turboprop engine. Use sketches and plots.
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Explain the concept of afterburning with the help of neat sketches.
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Explain briefly the different types of drags associated with an airplane.
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Plot the variation of Thrust required with flight velocity in steady level flight and give a brief explanation.
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Explain what drag divergence Mach number is. Also show the effect of drag divergence on maximum and minimum velocity parameter.
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An airplane is flying steady and level at a speed which is n times the minimum power speed. Show that the power ratio P/Pmin = (3+ n4)/4n, Where P is the power required corresponding to flight speed and Pmin is the minimum power required at the altitude.
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Write the equation of motion for maneuvering flight.
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Derive equation to obtain turn rate during a pull down maneuver.
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An airplane has a mass of 1200 Kg. It is turning on a horizontal circle of radius 120 m at airspeed of 45 m/s. The altitude of flight is 5 km (density = 0.77 kg/m3). Calculate the centripetal force responsible for the turn, acceleration of the airplane, correct bank angle and lift produced during the turn.
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Explain how the weight of the aircraft, the wind directions, and runway conditions affects the take-off performance.
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What are the safety factors that are to be considered while estimation the take-off performance? Explain in brief.
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Discuss in detail the following terms related to fuel planning:
Reserved fuel and Trip fuel
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Tankering.
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