Assignment III

```Introduction to Airplane Performance
Assignment – Week 3
1. Suppose an aircraft is flying in such atmosphere that there is no wind. As altitude increases, how
Mach number changes for same speed.
Ans : a
a. Increases.
b. Decreases.
c. Remains unchanged.
d. Insufficient data.
2. For same speed as altitude increases how Reynold’s number and viscosity of flow changes
respectively.
Ans : b
a. Increases, increases.
b. Decreases, decreases.
c. Decreases, increases.
d. Increases, decreases.
3. Under same atmospheric conditions when landing gears are taken in from out position. Among
πΆπ·0 πππ π which will change significantly ?
Ans : b
a. π.
b. πΆπ·0 .
c. Both equal.
d. Can’t say.
4. A low speed aircraft while tested under same aerodynamic conditions in a wind tunnel, what we
duplicate for dynamic similarity point of view.
Ans : a, d
a.
b.
c.
d.
Reynolds number.
Mach number.
Angle of attack.
Ratio of inertia to viscous force.
5. In 2D aerofoil πΆπ increases with angle of attack. This increment is due to increment in :
ans : c
a. Only induced drag.
b. Only skin friction.
c. Only flow separation.
d. Induced drag and skin friction.
6. In following figure for a given altitude power available and power required Vs velocity plot is
given. At which velocity the rate of climb will be maximum?
Ans : c
A
a.
b.
c.
d.
7.
B
C
D
A
B
C
D
Which of the following parameters can be read from the parabolic polar diagram of an
airplane?
Ans : d
a. The aspect ratio of the wing and the induced drag coefficient.
b. The minimum rate of descent and the induced drag.
c. The induced drag and the parasite drag.
d. The minimum glide angle and the parasite drag coefficient.
Data for question 8 to 12
Drag polar of an aircraft is given by
πΆπ· = .020 + .019 πΆπΏ2
and
8. What is the value of parasite drag coefficient?
a. 0.020
b. 0.019
c. 1.052
d. 1.025
9.
πΆπΏ
πΆπ·
is maximum for πΆπΏ =
a.
b.
c.
d.
10.
πΆπΏ 3/2
πΆπ·
Ans : c
1.052
1.777
1.025
Insufficient data
is maximum for πΆπΏ =
a.
b.
c.
d.
Ans : a
Ans : b
1.052
1.777
3.157
Insufficient data
11. For thrust required minimum theoretically at what angle of attack the aircraft is flying? Is this
Ans : b
a.
b.
c.
d.
13 degree, yes
13 degree, no
22.6 degree, yes
22.6 degree, no
12. For power required minimum theoretically at what angle of attack the aircraft is flying? Is this