JNTU
JNTU B.Tech II AERODYNAMICS - I Previous Question Paper (April/May - 2023 - R18)
i) Question paper consists of Part A, Part B. ii) Part A is compulsory, which carries 25 marks. In Part A, Answer all questions. iii) In Part B, Answer any one question from each unit. Each question carries 10 marks and may have a, b as sub questions.
Part A
Write the relations for specific heats.
Answer
The specific heats are related to the gas constant R and the adiabatic index γ as follows:
Define angular velocity, strain rate, vorticity and dilatation of a fluid element.
Answer
Angular velocity is the rate of rotation of a fluid element about its axes. Strain rate represents the rate of deformation of a fluid element due to velocity gradients. Vorticity is defined as twice the angular velocity vector, expressed as the curl of the velocity field (∇ × V). Dilatation (or volumetric strain rate) is the rate of change of volume per unit volume, given by the divergence of the velocity field (∇ · V).
Define Kutta condition with the help of a diagram.
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What is meant by Magnus effect?
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For an elliptical lift distribution over a wing must the chord vary elliptically long the span? Justify your answer with proper reasoning.
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What are the limitations of lifting line theory?
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What do you mean by Non-lifting bodies?
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Which kind of drag is predominant in the flow over blunt body and that over a stream lines body?
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Differentiate between Symmetric and Un-symmetric airfoils.
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State Kutta Joukowsky’s theorem.
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Part B
State and derive the continuity equation for compressible flow in differential form.
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Is the streamlines and equipotential lines are orthogonal? Prove your statement.
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A long elliptical cylinder with thickness to chord ratio of 1:7 is placed with its major axis aligned with a uniform irrotational stream of 36 m/s. Calculate the perpendicular to each other?
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What is a stagnation point and stagnation property? Derive equations for stagnation temperature, pressure and density.
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Explain source, sink, free and forced vortex with neat sketches.
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Show that the combination of uniform flow and doublet flow is equivalent to a non-lifting flow over a cylinder. Obtain the expression for velocity potential function and stream function for the combination.
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Explain the drag of a two- dimensional body using momentum equation.
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How we can synthesize the lifting flow over a circular cylinder? Explain with the sketches how the stream line pattern and stagnation points changes for different values of circulation.
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Explain the terms ‘Bound vortex’, ‘Starting vortex’ and ‘ Horse shoe vortex’.
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State Biot-Savart law and derive an expression for a velocity induced by an infinite vortex filament at a point, which is at a distance n from the filament.
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What is Rankine oval? What combination of flows are required to obtain oval?
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How does down wash affect the aerodynamics characteristic of a finite wing? Derive an expression for downwash using Prandtl’s lifting line theory?
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Explain the working principle of propeller. Explain the reason of propeller twist is more near root than tip.
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Illustrate the general considerations for Wing-body geometry. Sketch various wing-body configurations.
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Explain the flow past over Non-lifting bodies with suitable diagram.
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Describe the effect of curvature due to interferences on boundary layer development and flow separation with neat sketches.
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What are Karman-trefttz and von-mises airfoils? explain with neat sketches.
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Clearly explain the method of obtaining the Zoukowski transformation to get a cambered airfoil.
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List and explain the method of modeling fluid flow around airfoils using conformal transformation.
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Derive the Navier’s stokes equation for a cylindrical coordinate system.
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