hyper sonic aerodynamics

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Code No: 05422104 Set No. 1

JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABADIV B.Tech. II Sem., I Mid-Term Examinations, March – 2010

HYPERSONIC AERODYNAMICSObjective Exam

Name: ______________________________ Hall Ticket No.

Answer All Questions. All Questions Carry Equal Marks.Time: 20 Min. Marks: 20.

I Choose the correct alternative:

1. Main characteristic(s) of Hypersonic flow - [ ](A) thin shock layer, strong entropy gradient, viscous dissipation of kinetic energy in boundary

layer

(B) high temperature (C) strong shock (D) high Mach number

2. Continuity equation - [ ]

(A) (B)

(D) ( ) 0 DEL x V t

ρ ρ

∂− =

∂ (C)

3. Euler equation in x- direction [ ]

(A) (B)

(D)(C)

4. Wall boundary condition is [ ]

(A) (B) (C) (D)

5. In a hypersonic flow, [ ]

(A) the shock wave is very near the body (B) the shock wave is unstable

(C) the shock wave is very far from the body

(D) the volume between the shock wave and the body is very large.

6. According to Newtonian – Busemann theory, the pressure coefficient over a slender body of

revolution is given by In this equation, k stands for [ ]

(A) curvature of the surface of the bodes (B) thermal conductivity

(C) thermal diffusivity (D) Boltzmann constant

7. In the tangent wedge method for hypersonic flows, [ ](A) local flow at a point on the body is assumed to be the same as the flow over a tangent wedge at

that point.

(B) the body is replaced by a tangent at the nose.(C) local flow is along the tangent at the point (D) a body is replaced by a wedge.

Cont…..2

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Code No. 05422104 :2: Set No.1

8. The reduction in the velocity in the y direction across an oblique shock in a hypersonic flow tends

to be proportional to [ ](A) local flow deflection angle (B) square of local flow deflection angle

(C) proportional to the Mach number (D) proportional to square of Mach number

9. If u and v are the components of velocity at a point in the hypersonic flow over a body in the x andy directions, [ ]

(A) (B) (C) (D)

10. Prandtl number Pr is given by [ ]

(A) (B) (C) (D)

II Fill in the blanks:

11. Continuity equation in terms of the substantial derivative is ………………

12. Momentum equation in x – direction in terms of substantial derivative is ………………..

13. The shock angle for a hypersonic flow of Mach No. 36 over a wedge of 15 degree is ……

14. From Newtonian theory, for a very large Mach number, the pressure coefficient over a flat plate isgiven by

15. The pressure coefficient over a wedge is …………….. than over a cone of the same angle.

16. In the hypersonic flow across an oblique shock wave on a slender body, the y component of the

velocity v is changed ………………… than the x component u.

17. In the case of hypersonic flow across an oblique shock wave on a slender body, the ratio of reduction in the x component of the velocity, u, to the reduction in the y component of the

velocity, v, (in terms of gamma and the local flow deflection angle, Theta) is …………………

18. If u and v are the components of the velocity at a point in the hypersonic flow over a body, the

ratio of the components, in terms of gamma and shock angle β, is

19. The hypersonic similarity parameter is ……………….

20. Nusselt number is given by ………….

-oOo-

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Code No: 05422104 Set No. 2JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD

IV B.Tech. II Sem., I Mid-Term Examinations, March – 2010HYPERSONIC AERODYNAMICS

Objective ExamName: ______________________________ Hall Ticket No.




(A) (B) (C) (D)



(C) the shock wave is very far from the body(D) the volume between the shock wave and the body is very large.

3. According to Newtonian – Busemann theory, the pressure coefficient over a slender body of revolution is given by In this equation, k stands for [ ]



4. In the tangent wedge method for hypersonic flows, [ ]

(A) local flow at a point on the body is assumed to be the same as the flow over a tangent wedge at

that point.(B) the body is replaced by a tangent at the nose.

(C) local flow is along the tangent at the point (D) a body is replaced by a wedge.

5. The reduction in the velocity in the y direction across an oblique shock in a hypersonic flow tendsto be proportional to [ ]

(A) local flow deflection angle (B) square of local flow deflection angle


6. If u and v are the components of velocity at a point in the hypersonic flow over a body in the x and

y directions, [ ]

(A) (B) (C) (D)


(A) (B) (C) (D)

8. Main characteristic(s) of Hypersonic flow - [ ](A) thin shock layer, strong entropy gradient, viscous dissipation of kinetic energy in boundary

layer


Cont…..2

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Code No. 05422104 :2: Set No.2


(A) (B)

(D) ( ) 0 DEL x V t

ρ ρ

∂− =

∂ (C)


(A) (B)

(D)(C)






14. In the case of hypersonic flow across an oblique shock wave on a slender body, the ratio of

reduction in the x component of the velocity, u, to the reduction in the y component of thevelocity, v, (in terms of gamma and the local flow deflection angle, Theta) is …………………








-oOo-

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(A) curvature of the surface of the bodes (B) thermal conductivity(C) thermal diffusivity (D) Boltzmann constant

2. In the tangent wedge method for hypersonic flows, [ ](A) local flow at a point on the body is assumed to be the same as the flow over a tangent wedge at

that point.

(B) the body is replaced by a tangent at the nose.(C) local flow is along the tangent at the point (D) a body is replaced by a wedge.


to be proportional to [ ]

(A) local flow deflection angle (B) square of local flow deflection angle(C) proportional to the Mach number (D) proportional to square of Mach number


(A) (B) (C) (D)


(A) (B) (C) (D)

6. Main characteristic(s) of Hypersonic flow - [ ]

(A) thin shock layer, strong entropy gradient, viscous dissipation of kinetic energy in boundarylayer



(A) (B)

(D) ( ) 0 DEL x V t

ρ ρ

∂− =

∂ (C)

Cont…..2

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Code No. 05422104 :2: Set No.3


(A) (B)

(D)(C)


(A) (B) (C) (D)


(A) the shock wave is very near the body (B) the shock wave is unstable(C) the shock wave is very far from the body

(D) the volume between the shock wave and the body is very large.













19. From Newtonian theory, for a very large Mach number, the pressure coefficient over a flat plate is

given by


-oOo-

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to be proportional to [ ](A) local flow deflection angle (B) square of local flow deflection angle



(A) (B) (C) (D)


(A) (B) (C) (D)

4. Main characteristic(s) of Hypersonic flow - [ ]

(A) thin shock layer, strong entropy gradient, viscous dissipation of kinetic energy in boundarylayer



(A) (B)

(D) ( ) 0 DEL x V t

ρ ρ

∂− =

∂ (C)


(A) (B)

(D)(C)


(A) (B) (C) (D)

Cont…..2

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Code No. 05422104 :2: Set No.4



(C) the shock wave is very far from the body(D) the volume between the shock wave and the body is very large.





10. In the tangent wedge method for hypersonic flows, [ ]

(A) local flow at a point on the body is assumed to be the same as the flow over a tangent wedge at

that point.(B) the body is replaced by a tangent at the nose.

(C) local flow is along the tangent at the point (D) a body is replaced by a wedge.















-oOo-

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hyper sonic aerodynamics

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