1. Code No: 55069 Set No. 1
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
III B.Tech. I Sem., I Mid-Term Examinations, September – 2011
FLIGHT MECHANICS-II
Objective Exam
Name: ______________________________ Hall Ticket No. A
Answer All Questions. All Questions Carry Equal Marks.Time: 20 Min. Marks: 10.
I Choose the correct alternative:
⎛ dcM ⎞
1. ⎜ ⎟ = [ ]
⎝ dcL ⎠ wing
⎛ ⎞ ⎛ ⎞
xa ⎜ 2 0.035 ⎟ za xa ⎜ 2 0.035 ⎟ za
A. + CL ⎜ − ⎟ B. − CL ⎜ − ⎟
c ⎜ ΠeA dcL ⎟ c c ⎜ ΠeA dcL ⎟ c
⎝ da ⎠ ⎝ da ⎠
⎛ ⎞ ⎛ ⎞
xa ⎜ 2 0.035 ⎟ za xa ⎜ 2 0.035 ⎟ za
C. + CL ⎜ + ⎟ D. − CL ⎜ + ⎟
c ⎜ ΠeA dcL ⎟ c c ⎜ ΠeA dcL ⎟ c
⎝ da ⎠ ⎝ da ⎠
2. The parameter affected by the elevator deflection is [ ]
A. Wing AOA B. Elevator AOA C. Tail AOA D. empennage AOA
3. Effect of rudder deflection [ ]
A. Lateral control B. Longitudinal control C. Directional control D. None of the above
4. As the C.G moves forward aircraft becomes [ ]
A. more stable B. unstable C. No effect D. none of the above.
5. When the moment about center of gravity is zero then airplane is said to be [ ]
A. Trimmed B. Stable C. Unstable D. None
6. Pitching moment is due to [ ]
A. elevator deflection B. Flap deflection C. Aileron deflection D. Rudder
7. The effective angle of attack of the horizontal stabilize is given by α t = [ ]
A. α t = (αw-ε-iw-it+τδe) B. α t = (αw-ε-iw+it+τδe)
C. α t = (αw-ε-iw-it-τδe) D. α t = (αw+ε+iw+it+τδe)
8. The equation for static longitudinal stability stick free props off is [ ]
A. (dCm / dCL) free = (Xa / C) + (dCm / dCL) fus, nac – (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
B. (dCm / dCL) free = (Xa / C) - (dCm / dCL) fus, nac – (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
C . (dCm / dCL) free = (Xa / C) + (dCm / dCL) fus, nac +(at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
D. (dCm / dCL) free = (Xa / C) - (dCm / dCL) fus, nac + (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
Cont……2

2. Code No: 55069 :2: Set No. 1
9. Sideslip angle causes increase of the airplane’s [ ]
A. lift B. thrust C. height D. drag
10. The stick force gradient is the measure of the change in stick force needed to change the [ ]
A. Speed of the airplane B. Velocity of Airplane
C. Position of airplane D. Angle of airplane
II Fill in the blanks
11. For the airplane to be stable the slope of the CM versus CL curve must be _______________
12. Magnitude of the moment coefficient obtained per degree deflection of the elevator is known
as___________
13. The expression for rate of change of elevator angle with equilibrium lift coefficient is given by
dδe/dCL=______________
14. The term (δe/lsδs) is called the ___________________
15. For level and unaccelerated flight all the forces are in_________________
16. Tail efficiency ηt is given by ___________
17. The static force to be applied by the pilot, (when considering a push force as positive) can be
written as FS =________________
18. The relationship between the aero plane angular velocity (q), the forward velocity (v) and the
airplane load factor (n) for steady level turns is given by ___________
19. The point on the airfoil at which the aerodynamic moment is independent of the AOA is called
___________
20. For static stability, the center of gravity must lie ________ of the neutral point.
-oOo-

3. Code No: 55069 Set No. 2
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
III B.Tech. I Sem., I Mid-Term Examinations, September – 2011
FLIGHT MECHANICS-II
Objective Exam
Name: ______________________________ Hall Ticket No. A
Answer All Questions. All Questions Carry Equal Marks.Time: 20 Min. Marks: 10.
I Choose the correct alternative:
1. As the C.G moves forward aircraft becomes [ ]
A. more stable B. unstable C. No effect D. none of the above.
2. When the moment about center of gravity is zero then airplane is said to be [ ]
A. Trimmed B. Stable C. Unstable D. None
3. Pitching moment is due to [ ]
A. elevator deflection B. Flap deflection C. Aileron deflection D. Rudder
4. The effective angle of attack of the horizontal stabilize is given by α t = [ ]
A. α t = (αw-ε-iw-it+τδe) B. α t = (αw-ε-iw+it+τδe)
C. α t = (αw-ε-iw-it-τδe) D. α t = (αw+ε+iw+it+τδe)
5. The equation for static longitudinal stability stick free props off is [ ]
A. (dCm / dCL) free = (Xa / C) + (dCm / dCL) fus, nac – (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
B. (dCm / dCL) free = (Xa / C) - (dCm / dCL) fus, nac – (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
C . (dCm / dCL) free = (Xa / C) + (dCm / dCL) fus, nac +(at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
D. (dCm / dCL) free = (Xa / C) - (dCm / dCL) fus, nac + (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
6. Sideslip angle causes increase of the airplane’s [ ]
A. lift B. thrust C. height D. drag
7. The stick force gradient is the measure of the change in stick force needed to change the [ ]
A. Speed of the airplane B. Velocity of Airplane
C. Position of airplane D. Angle of airplane
⎛ dcM ⎞
8. ⎜ ⎟ = [ ]
⎝ dcL ⎠ wing
⎛ ⎞ ⎛ ⎞
xa ⎜ 2 0.035 ⎟ za xa ⎜ 2 0.035 ⎟ za
A. + CL ⎜ − ⎟ B. − CL ⎜ − ⎟
c ⎜ ΠeA dcL ⎟ c c ⎜ ΠeA dcL ⎟ c
⎝ da ⎠ ⎝ da ⎠
⎛ ⎞ ⎛ ⎞
xa ⎜ 2 0.035 ⎟ za xa ⎜ 2 0.035 ⎟ za
C. + CL ⎜ + ⎟ D. − CL ⎜ + ⎟
c ⎜ ΠeA dcL ⎟ c c ⎜ ΠeA dcL ⎟ c
⎝ da ⎠ ⎝ da ⎠
Cont……2

4. Code No: 55069 :2: Set No. 2
9. The parameter affected by the elevator deflection is [ ]
A. Wing AOA B. Elevator AOA C. Tail AOA D. empennage AOA
10. Effect of rudder deflection [ ]
A. Lateral control B. Longitudinal control C. Directional control D. None of the above
II Fill in the blanks
11. The term (δe/lsδs) is called the ___________________
12. For level and unaccelerated flight all the forces are in_________________
13. Tail efficiency ηt is given by ___________
14. The static force to be applied by the pilot, (when considering a push force as positive) can be
written as FS =________________
15. The relationship between the aero plane angular velocity (q), the forward velocity (v) and the
airplane load factor (n) for steady level turns is given by ___________
16. The point on the airfoil at which the aerodynamic moment is independent of the AOA is called
___________
17. For static stability, the center of gravity must lie ________ of the neutral point.
18. For the airplane to be stable the slope of the CM versus CL curve must be _______________
19. Magnitude of the moment coefficient obtained per degree deflection of the elevator is known
as___________
20. The expression for rate of change of elevator angle with equilibrium lift coefficient is given by
dδe/dCL=______________
-oOo-

5. Code No: 55069 Set No. 3
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
III B.Tech. I Sem., I Mid-Term Examinations, September – 2011
FLIGHT MECHANICS-II
Objective Exam
Name: ______________________________ Hall Ticket No. A
Answer All Questions. All Questions Carry Equal Marks.Time: 20 Min. Marks: 10.
I Choose the correct alternative:
1. Pitching moment is due to [ ]
A. elevator deflection B. Flap deflection C. Aileron deflection D. Rudder
2. The effective angle of attack of the horizontal stabilize is given by α t = [ ]
A. α t = (αw-ε-iw-it+τδe) B. α t = (αw-ε-iw+it+τδe)
C. α t = (αw-ε-iw-it-τδe) D. α t = (αw+ε+iw+it+τδe)
3. The equation for static longitudinal stability stick free props off is [ ]
A. (dCm / dCL) free = (Xa / C) + (dCm / dCL) fus, nac – (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
B. (dCm / dCL) free = (Xa / C) - (dCm / dCL) fus, nac – (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
C . (dCm / dCL) free = (Xa / C) + (dCm / dCL) fus, nac +(at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
D. (dCm / dCL) free = (Xa / C) - (dCm / dCL) fus, nac + (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
4. Sideslip angle causes increase of the airplane’s [ ]
A. lift B. thrust C. height D. drag
5. The stick force gradient is the measure of the change in stick force needed to change the [ ]
A. Speed of the airplane B. Velocity of Airplane
C. Position of airplane D. Angle of airplane
⎛ dcM ⎞
6. ⎜ ⎟ = [ ]
⎝ dcL ⎠ wing
⎛ ⎞ ⎛ ⎞
xa ⎜ 2 0.035 ⎟ za xa ⎜ 2 0.035 ⎟ za
A. + CL ⎜ − ⎟ B. − CL ⎜ − ⎟
c ⎜ ΠeA dcL ⎟ c c ⎜ ΠeA dcL ⎟ c
⎝ da ⎠ ⎝ da ⎠
⎛ ⎞ ⎛ ⎞
xa ⎜ 2 0.035 ⎟ za xa ⎜ 2 0.035 ⎟ za
C. + CL ⎜ + ⎟ D. − CL ⎜ + ⎟
c ⎜ ΠeA dcL ⎟ c c ⎜ ΠeA dcL ⎟ c
⎝ da ⎠ ⎝ da ⎠
7. The parameter affected by the elevator deflection is [ ]
A. Wing AOA B. Elevator AOA C. Tail AOA D. empennage AOA
8. Effect of rudder deflection [ ]
A. Lateral control B. Longitudinal control C. Directional control D. None of the above
Cont……2

6. Code No: 55069 :2: Set No. 3
9. As the C.G moves forward aircraft becomes [ ]
A. more stable B. unstable C. No effect D. none of the above.
10. When the moment about center of gravity is zero then airplane is said to be [ ]
A. Trimmed B. Stable C. Unstable D. None
II Fill in the blanks
11. Tail efficiency ηt is given by ___________
12. The static force to be applied by the pilot, (when considering a push force as positive) can be
written as FS =________________
13. The relationship between the aero plane angular velocity (q), the forward velocity (v) and the
airplane load factor (n) for steady level turns is given by ___________
14. The point on the airfoil at which the aerodynamic moment is independent of the AOA is called
___________
15. For static stability, the center of gravity must lie ________ of the neutral point.
16. For the airplane to be stable the slope of the CM versus CL curve must be _______________
17. Magnitude of the moment coefficient obtained per degree deflection of the elevator is known
as___________
18. The expression for rate of change of elevator angle with equilibrium lift coefficient is given by
dδe/dCL=______________
19. The term (δe/lsδs) is called the ___________________
20. For level and unaccelerated flight all the forces are in_________________
-oOo-

7. Code No: 55069 Set No. 4
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
III B.Tech. I Sem., I Mid-Term Examinations, September – 2011
FLIGHT MECHANICS-II
Objective Exam
Name: ______________________________ Hall Ticket No. A
Answer All Questions. All Questions Carry Equal Marks.Time: 20 Min. Marks: 10.
I Choose the correct alternative:
1. The equation for static longitudinal stability stick free props off is [ ]
A. (dCm / dCL) free = (Xa / C) + (dCm / dCL) fus, nac – (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
B. (dCm / dCL) free = (Xa / C) - (dCm / dCL) fus, nac – (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
C . (dCm / dCL) free = (Xa / C) + (dCm / dCL) fus, nac +(at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
D. (dCm / dCL) free = (Xa / C) - (dCm / dCL) fus, nac + (at/aw V η t (1-(dε/dα))) ((1-Chα / Chδ) τ)
2. Sideslip angle causes increase of the airplane’s [ ]
A. lift B. thrust C. height D. drag
3. The stick force gradient is the measure of the change in stick force needed to change the [ ]
A. Speed of the airplane B. Velocity of Airplane
C. Position of airplane D. Angle of airplane
⎛ dcM ⎞
4. ⎜ ⎟ = [ ]
⎝ dcL ⎠ wing
⎛ ⎞ ⎛ ⎞
xa ⎜ 2 0.035 ⎟ za xa ⎜ 2 0.035 ⎟ za
A. + CL ⎜ − ⎟ B. − CL ⎜ − ⎟
c ⎜ ΠeA dcL ⎟ c c ⎜ ΠeA dcL ⎟ c
⎝ da ⎠ ⎝ da ⎠
⎛ ⎞ ⎛ ⎞
xa ⎜ 2 0.035 ⎟ za xa ⎜ 2 0.035 ⎟ za
C. + CL ⎜ + ⎟ D. − CL ⎜ + ⎟
c ⎜ ΠeA dcL ⎟ c c ⎜ ΠeA dcL ⎟ c
⎝ da ⎠ ⎝ da ⎠
5. The parameter affected by the elevator deflection is [ ]
A. Wing AOA B. Elevator AOA C. Tail AOA D. empennage AOA
6. Effect of rudder deflection [ ]
A. Lateral control B. Longitudinal control C. Directional control D. None of the above
7. As the C.G moves forward aircraft becomes [ ]
A. more stable B. unstable C. No effect D. none of the above.
8. When the moment about center of gravity is zero then airplane is said to be [ ]
A. Trimmed B. Stable C. Unstable D. None
Cont……2

8. Code No: 55069 :2: Set No. 4
9. Pitching moment is due to [ ]
A. elevator deflection B. Flap deflection C. Aileron deflection D. Rudder
10. The effective angle of attack of the horizontal stabilize is given by α t = [ ]
A. α t = (αw-ε-iw-it+τδe) B. α t = (αw-ε-iw+it+τδe)
C. α t = (αw-ε-iw-it-τδe) D. α t = (αw+ε+iw+it+τδe)
II Fill in the blanks
11. The relationship between the aero plane angular velocity (q), the forward velocity (v) and the
airplane load factor (n) for steady level turns is given by ___________
12. The point on the airfoil at which the aerodynamic moment is independent of the AOA is called
___________
13. For static stability, the center of gravity must lie ________ of the neutral point.
14. For the airplane to be stable the slope of the CM versus CL curve must be _______________
15. Magnitude of the moment coefficient obtained per degree deflection of the elevator is known
as___________
16. The expression for rate of change of elevator angle with equilibrium lift coefficient is given by
dδe/dCL=______________
17. The term (δe/lsδs) is called the ___________________
18. For level and unaccelerated flight all the forces are in_________________
19. Tail efficiency ηt is given by ___________
20. The static force to be applied by the pilot, (when considering a push force as positive) can be
written as FS =________________
-oOo-