Code No: 24045

RR

Set No - 1

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JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD II B.TECH II SEM SUPPLEMENTARY EXAMINATIONS FEBRUARY 2010 - 2010 II B.Tech II Semester Supplimentary Examinations,February AERODYNAMICS - I Aeronautical Engineering Time: 3 hours Max Marks: 80 Answer any FIVE Questions All Questions carry equal marks ????? 1. Sketch and explain flow patterns around a helicopter in forward flight mode. How are the aerodynamic forces balanced in each case? [16]

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2. Apply the Kutta-Zhukovsky transformation to obtain a symmetrical airfoil of thickness ratio 15%. Make use of sketches and plots to elaborate your answer. [16]

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3. The following data are determined from an airfoil test with respect to a point located at 20 % of the chord located from the leading edge: At CL = 0, CM = -0.04; at α = 50 , CL = 0.7 , CD = 0.05; CM = -0.016. Where is the aerodynamic center located? [16] 4. Define the term Thrust coefficient. Hence develop an expression for it from dimensional analysis.

[16]

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5. Describe various types of airfoil sections used in aircraft industry. Describe in details 4 digit and 5 digit series of NACA sections. Make use of sketches and c1 -cd -α plots to illustrate your answer. [16] 6. Show that the Complex Potential function w =Az n represents flow in a corner of angle π /n . Sketch the streamlines and equipotential lines. [16]

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7. Define total drag acting on an airplane and its components. What are the causes of each of these components? Compare the total drag acting on a Jumbo jet and that on a supersonic fighter plane. Make use of sketches /plots to illustrate your answer. [16]

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8. An airscrew is required to produce thrust of 4500 Newtons at a speed of 130 m/s at sea level. The diameter of the disc is 2.8 m. Estimate the minimum power to be supplied on the basis of ideal actuator disc. Another propeller is placed in its slipstream such that its disc area is just equal to that of the slipstream. Work out the size ant input power to the second propeller on the basis of Froude momentum theory. [16] ?????

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Set No - 2

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Code No: 24045 JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD II B.TECH II SEM SUPPLEMENTARY EXAMINATIONS FEBRUARY - 2010 II B.Tech II Semester Semester Supplimentary Examinations,February 2010 AERODYNAMICS - I Aeronautical Engineering Time: 3 hours

Max Marks: 80

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Answer any FIVE Questions All Questions carry equal marks ?????

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1. Describe various types of airfoil sections used in aircraft industry. Describe in details 4 digit and 5 digit series of NACA sections. Make use of sketches and c1 -cd -α plots to illustrate your answer. [16] 2. Define the term Thrust coefficient. Hence develop an expression for it from dimensional analysis.

[16]

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3. Define total drag acting on an airplane and its components. What are the causes of each of these components? Compare the total drag acting on a Jumbo jet and that on a supersonic fighter plane. Make use of sketches /plots to illustrate your answer. [16]

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4. An airscrew is required to produce thrust of 4500 Newtons at a speed of 130 m/s at sea level. The diameter of the disc is 2.8 m. Estimate the minimum power to be supplied on the basis of ideal actuator disc. Another propeller is placed in its slipstream such that its disc area is just equal to that of the slipstream. Work out the size ant input power to the second propeller on the basis of Froude momentum theory. [16] 5. Sketch and explain flow patterns around a helicopter in forward flight mode. How are the aerodynamic forces balanced in each case? [16]

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6. Apply the Kutta-Zhukovsky transformation to obtain a symmetrical airfoil of thickness ratio 15%. Make use of sketches and plots to elaborate your answer. [16]

Aj

7. The following data are determined from an airfoil test with respect to a point located at 20 % of the chord located from the leading edge: At CL = 0, CM = -0.04; at α = 50 , CL = 0.7 , CD = 0.05; CM = -0.016. Where is the aerodynamic center located? [16] 8. Show that the Complex Potential function w =Az n represents flow in a corner of angle π /n . Sketch the streamlines and equipotential lines. [16] ?????

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Code No: 24045

RR

Set No - 3

in

JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD II B.TECH SEM SUPPLEMENTARY EXAMINATIONS FEBRUARY - 20102010 II B.Tech II II Semester Semester Supplimentary Examinations,February AERODYNAMICS - I Aeronautical Engineering Time: 3 hours Max Marks: 80 Answer any FIVE Questions All Questions carry equal marks ?????

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1. Define total drag acting on an airplane and its components. What are the causes of each of these components? Compare the total drag acting on a Jumbo jet and that on a supersonic fighter plane. Make use of sketches /plots to illustrate your answer. [16]

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2. An airscrew is required to produce thrust of 4500 Newtons at a speed of 130 m/s at sea level. The diameter of the disc is 2.8 m. Estimate the minimum power to be supplied on the basis of ideal actuator disc. Another propeller is placed in its slipstream such that its disc area is just equal to that of the slipstream. Work out the size ant input power to the second propeller on the basis of Froude momentum theory. [16] 3. Apply the Kutta-Zhukovsky transformation to obtain a symmetrical airfoil of thickness ratio 15%. Make use of sketches and plots to elaborate your answer. [16]

uW

4. The following data are determined from an airfoil test with respect to a point located at 20 % of the chord located from the leading edge: At CL = 0, CM = -0.04; at α = 50 , CL = 0.7 , CD = 0.05; CM = -0.016. Where is the aerodynamic center located? [16] 5. Sketch and explain flow patterns around a helicopter in forward flight mode. How are the aerodynamic forces balanced in each case? [16]

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6. Describe various types of airfoil sections used in aircraft industry. Describe in details 4 digit and 5 digit series of NACA sections. Make use of sketches and c1 -cd -α plots to illustrate your answer. [16]

Aj

7. Show that the Complex Potential function w =Az n represents flow in a corner of angle π /n . Sketch the streamlines and equipotential lines. [16] 8. Define the term Thrust coefficient. Hence develop an expression for it from dimensional analysis. ?????

3

[16]

Code No: 24045

RR

Set No - 4

in

JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD II B.TECH II SEM SUPPLEMENTARY EXAMINATIONS FEBRUARY - 2010 II B.Tech II Semester Semester Supplimentary Examinations,February 2010 AERODYNAMICS - I Aeronautical Engineering Time: 3 hours Max Marks: 80 Answer any FIVE Questions All Questions carry equal marks ????? 1. Define the term Thrust coefficient. Hence develop an expression for it from dimensional analysis.

[16]

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2. An airscrew is required to produce thrust of 4500 Newtons at a speed of 130 m/s at sea level. The diameter of the disc is 2.8 m. Estimate the minimum power to be supplied on the basis of ideal actuator disc. Another propeller is placed in its slipstream such that its disc area is just equal to that of the slipstream. Work out the size ant input power to the second propeller on the basis of Froude momentum theory. [16]

3. Describe various types of airfoil sections used in aircraft industry. Describe in details 4 digit and 5 digit series of NACA sections. Make use of sketches and c1 -cd -α plots to illustrate your answer. [16]

uW

4. Show that the Complex Potential function w =Az n represents flow in a corner of angle π /n . Sketch the streamlines and equipotential lines. [16] 5. Apply the Kutta-Zhukovsky transformation to obtain a symmetrical airfoil of thickness ratio 15%. Make use of sketches and plots to elaborate your answer. [16] 6. Sketch and explain flow patterns around a helicopter in forward flight mode. How are the aerodynamic forces balanced in each case? [16]

nt

7. Define total drag acting on an airplane and its components. What are the causes of each of these components? Compare the total drag acting on a Jumbo jet and that on a supersonic fighter plane. Make use of sketches /plots to illustrate your answer. [16]

Aj

8. The following data are determined from an airfoil test with respect to a point located at 20 % of the chord located from the leading edge: At CL = 0, CM = -0.04; at α = 50 , CL = 0.7 , CD = 0.05; CM = -0.016. Where is the aerodynamic center located? [16] ?????

4