3RD YEAR SEMESTER 1 SUPPLEMENTARY JNTU B.TECH ENGINEERING QUESTION PAPER - AERODYNAMICS – II

RR                    SET-1

JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD III B.TECH – I SEM SUPPLEMENTARY EXAMINATIONS, JUNE - 2010

AERODYNAMICS – II (AERONAUTICAL ENGINEERING)

Time: 3hours                                                                                     Max.Marks:80

Answer any FIVE questions

All questions carry equal marks

- - -

1.         What are the different fluid models we use in aerodynamics? Explain them? What are the types of governing equations? How these are related to fluid models?  [16]

2.         Show that for incompressible flow over a 2D body, drag can be estimated by

b

D ' = ρa ∫ u2 (u1  − u2 ) dy .                                                                                     [16]

3.         Show that the Bernoulli’s equation is a statement of Newton’s second law for a steady, inviscid, incompressible flow with no body force?                                [16]

4.         A sink of strength of 120 m2/s is situated 2 m downstream from a source of equal strength in an irrotational uniform stream of 30 m/s. Find the fineness ratio of the oval formed by the stream line ψ = 0 [16]

5.         Explain the Kelvin’s circulation theorem? What is a starting vortex and how it is generated?                                                                                                           [16]

 6.         A NACA 0012 airfoil is kept in a free stream of velocity 100 m/s at the sea level.

Can  we  apply  thin  airfoil  theory  to  this  airfoil?  Justify  you  answer  with appropriate answers. What are the assumptions in thin airfoil theory? What is lift generated by the airfoil if the chord of the airfoil is 2m?                                   [16]

7.         Explain the following:

a)        Wing tip vortices, downwash

b)        Induced AoA and Induced drag

c)        Span wise lift distribution over a finite wing.                                         [16]

8.         Consider an airplane that weighs 10,700 N and cruises in level flight at 300 km/h at an altitude of 1000 m. The wing has a surface area of 17 square meters and an aspect ratio of 6.2. Assume that the lift coefficient is a linear function of the angle of attack and α L =0 = -1.2. If the load distribution is elliptic, calculate the value of the circulation at the centre of the wing, the downwash induced drag coefficient? Take density value at this altitude as 0.90748.                                                   [16]

*****

RR                    SET-2

JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD III B.TECH – I SEM SUPPLEMENTARY EXAMINATIONS, JUNE - 2010

AERODYNAMICS – II (AERONAUTICAL ENGINEERING)

Time: 3hours                                                                                     Max.Marks:80

Answer any FIVE questions

All questions carry equal marks

- - -

1.         Show that the Bernoulli’s equation is a statement of Newton’s second law for a steady, inviscid, incompressible flow with no body force?                                [16]

2.         A sink of strength of 120 m2/s is situated 2 m downstream from a source of equal strength in an irrotational uniform stream of 30 m/s. Find the fineness ratio of the oval formed by the stream line ψ = 0 [16]

3.         Explain the Kelvin’s circulation theorem? What is a starting vortex and how it is generated?                                                                                                           [16]

4.         A NACA 0012 airfoil is kept in a free stream of velocity 100 m/s at the sea level.

Can  we  apply  thin  airfoil  theory  to  this  airfoil?  Justify  you  answer  with appropriate answers. What are the assumptions in thin airfoil theory? What is lift generated by the airfoil if the chord of the airfoil is 2m?                                   [16]

5.         Explain the following:

a)        Wing tip vortices, downwash

b)        Induced AoA and Induced drag

c)        Span wise lift distribution over a finite wing.                                         [16]

6.         Consider an airplane that weighs 10,700 N and cruises in level flight at 300 km/h at an altitude of 1000 m. The wing has a surface area of 17 square meters and an aspect ratio of 6.2. Assume that the lift coefficient is a linear function of the angle of attack and α L =0 = -1.2. If the load distribution is elliptic, calculate the value of the circulation at the centre of the wing, the downwash induced drag coefficient? Take density value at this altitude as 0.90748.                                                   [16]

7.         What are the different fluid models we use in aerodynamics? Explain them? What are the types of governing equations? How these are related to fluid models?  [16]

8.         Show that for incompressible flow over a 2D body, drag can be estimated by

b

D ' = ρa ∫ u2 (u1  − u2 ) dy .                                                                                     [16]

*****

RR                    SET-3

JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD III B.TECH – I SEM SUPPLEMENTARY EXAMINATIONS, JUNE - 2010

AERODYNAMICS – II (AERONAUTICAL ENGINEERING)

Time: 3hours                                                                                     Max.Marks:80

Answer any FIVE questions

All questions carry equal marks

- - -

1.         Explain the Kelvin’s circulation theorem? What is a starting vortex and how it is generated?                                                                                                           [16]

2.         A NACA 0012 airfoil is kept in a free stream of velocity 100 m/s at the sea level.

Can  we  apply  thin  airfoil  theory  to  this  airfoil?  Justify  you  answer  with appropriate answers. What are the assumptions in thin airfoil theory? What is lift generated by the airfoil if the chord of the airfoil is 2m?                                   [16]

3.         Explain the following:

a)        Wing tip vortices, downwash

b)        Induced AoA and Induced drag

c)        Span wise lift distribution over a finite wing.                                         [16]

4.         Consider an airplane that weighs 10,700 N and cruises in level flight at 300 km/h at an altitude of 1000 m. The wing has a surface area of 17 square meters and an aspect ratio of 6.2. Assume that the lift coefficient is a linear function of the angle of attack and α L =0 = -1.2. If the load distribution is elliptic, calculate the value of the circulation at the centre of the wing, the downwash induced drag coefficient? Take density value at this altitude as 0.90748.                                                   [16]

5.         What are the different fluid models we use in aerodynamics? Explain them? What are the types of governing equations? How these are related to fluid models?  [16]

6.         Show that for incompressible flow over a 2D body, drag can be estimated by

b

D ' = ρa ∫ u2 (u1  − u2 ) dy .                                                                                     [16]

7.         Show that the Bernoulli’s equation is a statement of Newton’s second law for a steady, inviscid, incompressible flow with no body force?                                [16]

8.         A sink of strength of 120 m2/s is situated 2 m downstream from a source of equal strength in an irrotational uniform stream of 30 m/s. Find the fineness ratio of the

oval formed by the stream line ψ = 0            [16]

*****

RR                    SET-4

JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD III B.TECH – I SEM SUPPLEMENTARY EXAMINATIONS, JUNE - 2010

AERODYNAMICS – II (AERONAUTICAL ENGINEERING)

Time: 3hours                                                                                     Max.Marks:80

Answer any FIVE questions

All questions carry equal marks

- - -

1.         Explain the following:

a)        Wing tip vortices, downwash

b)        Induced AoA and Induced drag

c)        Span wise lift distribution over a finite wing.                                         [16]

2.         Consider an airplane that weighs 10,700 N and cruises in level flight at 300 km/h at an altitude of 1000 m. The wing has a surface area of 17 square meters and an aspect ratio of 6.2. Assume that the lift coefficient is a linear function of the angle of attack and α L =0 = -1.2. If the load distribution is elliptic, calculate the value of the circulation at the centre of the wing, the downwash induced drag coefficient? Take density value at this altitude as 0.90748.                                                   [16]

3.         What are the different fluid models we use in aerodynamics? Explain them? What are the types of governing equations? How these are related to fluid models?  [16]

4.         Show that for incompressible flow over a 2D body, drag can be estimated by

b

D ' = ρa ∫ u2 (u1  − u2 ) dy .                                                                                     [16]

5.         Show that the Bernoulli’s equation is a statement of Newton’s second law for a steady, inviscid, incompressible flow with no body force?                                [16]

6.         A sink of strength of 120 m2/s is situated 2 m downstream from a source of equal strength in an irrotational uniform stream of 30 m/s. Find the fineness ratio of the

oval formed by the stream line ψ = 0 [16]

7.         Explain the Kelvin’s circulation theorem? What is a starting vortex and how it is generated?                                                                                                           [16]

 8.         A NACA 0012 airfoil is kept in a free stream of velocity 100 m/s at the sea level.

Can  we  apply  thin  airfoil  theory  to  this  airfoil?  Justify  you  answer  with appropriate answers. What are the assumptions in thin airfoil theory? What is lift generated by the airfoil if the chord of the airfoil is 2m?                                   [16]

*****