JNTU
JNTU B.Tech IV BASICS OF AERONAUTICAL ENGINEERING Previous Question Paper (January/February - 2023 - R18)
Answer any five questions. Part A is compulsory. Part B: Answer any one question from each unit.
Part A
Answer all questions (25 Marks).
Show how pressure and density varies with altitude in graph?
Answer
In the standard atmosphere, both pressure and density decrease exponentially with increasing altitude. On a graph with altitude on the y-axis and pressure/density on the x-axis, the curves show a rapid decline near the surface, gradually flattening out as altitude increases toward the tropopause.
If the air pressure remained same and the air temperature is 70°F, what is the density of the air near the surface of the water?
Answer
Using the ideal gas law, density 𝜌 = P / (R × T). Given T = 70°F = 529.67°R and standard sea-level pressure P = 2116.2 lb/ft², the density is approximately 0.00233 slugs/ft³.
Define three-dimensional airflow with examples.
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What is a streamline flow explain with example?
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What are the main functions of NACA?
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How does wing loading affects performances and rate of climb of aircraft?
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What is downwash?
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Draw L/D curve for wing of an Aircraft.
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What are the types of aerodynamic flow?
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Why is it important to know the flow regime?
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Part B
Answer any one question from each unit (50 Marks).
Explain the structure of atmosphere by dividing into different layers.
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If an airplane is flying at an altitude where the actual pressure and temperature are 4.72 × 104 N/m2 and 255.7 K, respectively, what are the pressure, temperature, and density altitudes?
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At what value of the geometric altitude is the difference h - hG equal to 2 percent of the geo potential altitude, h?
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At 12 km in the standard atmosphere, the pressure, density, and temperature are 1.9399 × 104 N/m2, 3.1194 × 10-1 kg/m3, and 216.66 K, respectively. Using these values, calculate the standard atmospheric values of pressure, density, and temperature at an altitude of 18 km.
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Derive momentum equation in integral form and differential form by applying the physical principle to a suitable flow model.
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Consider an airplane flying with a velocity of 60 m/s at a standard altitude of 3 km. At a point on the wing, the airflow velocity is 70 m/s. Calculate the pressure at this point. Assume incompressible flow.
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The altimeter on a low-speed Cessna 150 private aircraft reads 5000 ft. By an independent measurement, the outside air temperature is 505° R. If a Pitot tube mounted on the wing tip measures a pressure of 1818 lb/ft2, what is the true velocity of the airplane? What is the equivalent airspeed?
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Explain in detail about vortex flow and generation of lift through circulation.
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Describe the aerodynamic moment for a positively and negatively cambered aerofoil.
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Discuss how drag coefficient varies with Mach number and how prediction of drag divergence Mach number is carried out.
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Why optimum wing shapes for supersonic flight are different than for subsonic flight.
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Compare and contrast the external configurations of a subsonic and a supersonic aircraft with the help of neat sketches.
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Explain the characteristics of the transonic and subsonic flow regimes.
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