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Aerodynamics II question paper (Anna university)

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Reg.No.,
~
Ques
ti
on Paper
Co
de
53013
B.E.IB.Tech. DEGREE EXAMINATION, NOVEMBERIDECEMBER 2010
Fifth
Semester
Aeronautical Engineering
AE 2303 -AERODYNAMICS -U
Regulation 2008)
Time:
Three hours
Maximum
: 100
Marks
Gas
Tables
permitted Answer
ALL
questions
PART A
00
x
2
=
2
Marks
I
Differentiate
perfect
gas
from
rea
l gases. 2. Why do you need a
convergent-divergent
nozzle
to accelerate
the
flow from subsonic to
supersonic
speed?
3
Define characteristic Mach number and give its maximum value
for
air
.
4
Define sbock
strength and
express
t
in
terms
of Mach
number
for a
normal
shock. 5.
State
the limiting
values
of
shock
wave
angle in
a
supersonic
flow for zero flow deflection. G.
Explain
Mach reflection.
7
What are Riemann
invariants?
8
Wntc
down
th
e
Prandtl-Glauert
similanty
rule
for
pre
ss
ure
coefficient
and
explam. 9
What
IS
c
ntlcal
M ach
number?
10
. De
sc
nbe
boundary
lay
er
fence
and
st
ate
Its
purpo
se.
PART B
5)
16
::
80
Mark
s)
11
. (a)
(i)
Derive
the
on
e
dimensional
adiabatic
s
teady
s
tat
e
energy
equation
and
de
duce
the
isentropic
relation
s for a
perfect
gas. (8)
(ii)
Air
fl
ow is disc
harged
to
atmosph
ere
at
sea
level
through
a
so
ni
c nozzle.
f
the
air
storage
at
the res
e
rvoir
is
40
)
O
N m~
de
termin
e
th
e pre
SS
\lr
e,
tem)Jerature
and
den
s
it
y
at
the
exit
of the
nozzle. Ass
um
e
that
the
reservoir
air
is
at
sea
level
temperature.
(8)
(b)
(i)
Explain
th
e
phen
omenon
of
choking
in
a nozzle
fl
ow
and
sh
ow
that
th
e
mass
flow
of
a
choked
nozz.l
e can be ex
pre
ssed
as
ã
A
m~0 6847~
RTo
(8)
)
A s
torag
e c
hamber
of a
co
mpressor
IS
maintam
ed
at
1.8
atmosphe
re
ahsolute
and 20 deg
re
e
C.
f
th
e s
urr
oundmg
pressure
IS I
atmosphere, calculate
the
velocity
with wh
ich
au
'
fl
ow
takes
pla
ce from
th
e c
hamber
to
outside thro\lgh
a
umt
ar
ea
hole. Also,
calcu
lat
e
the
mass
fl
ow
per unit
area,
Assume
air
as
a
perfect
gas
.
8)
1
2.
(a)
(i)
Derive
the
Raylei
gh supersonic
Pitot
f
ormula
.
8)
(b) (ii)
A
Pit
ot
tube
is
inserted in
to
an
ail' flow
of
Mach 2
where
th
e
sta
tic
pr
ess
ur
e
IS
1
atmo
s
phere
.
Calculate
the
total
pr
ess
ur
e
measured
by
th
e
tube
and
the
lo
ss
of total
pr
ess
ure
ex
peri
enced. (8)
(i)
0,
Derive a
relation
betwee
n flow
turning
angle, shock
Fre
e-s
tr
ea
m Mach
numb
er for ob
liqu
e shock
waves angle
and
8)
(ii)
Co
nsider a Mach 2.5 s
U)
Je
rsonic
fl
ow over a
co
mp
ress
ion
corner
with
a deflection
angle
of
14
d
eg
ree
.
Calculate
t
he
In
crease
m shock s
tr
eng
th
if the
deflection
angle
IS
doubled 10 28 c 'gree
and
give
your
oomments
on
the
sh
oc
k
wa\ e
cha
ra
cte
ri
stics (8) 13, (a) (i)
Explam
the
co
n
cept
of
Prandll·Me
yer expa
n
SIO
n
around
a
co
nvex
,
co
rn
e
l
and
represe
nt
t
in
Hodograllh
plane
(8)
(li)
A s
nperso
mc
fl
ow
at
MI
=
and
PI
=
1
atmosphere expands around
a s
harp
co
rn
er.
f
the
pr
ess
w'e down
st
r
eam
of
the
co
mer
IS
0.1306
atm.,
calc
ulat
e
the
de
fl
ect
ion angle
of the
corne
l
. (8)
0,
2
53013
(b) (i)
Explain the procedure
to
obtain supersonic
nozzle
contour
given Mach
number
using
Method
of characteristics.
for
:l
8)
(ii) An
incident
shock
wave angle
of
35
degree impinges
on a
straight
walL
f
the
upstream
flow properties
are
M
=
3,
P
=
1
atm. and
T
=
300
K,
calculate
the
reflected shock
wave angle with respect
to
the wall
and
the
flow properties
M,
P
and
T
downstream
of the
reflected shock wave.
(8)
14
.
a)
i)
Slate
the
assumptions
made
n
small perturbation
potential
theory
and
show
that
the linearized
pressure
coefficient
IS
a function of the
perturbation
veioClty in
the
mam
flow directIOn
on
ly.
(ii)
2
= .
V
Describe
Prandtl Glauert
affine
tranafofll1ation
over
airfoils
and
hIghlight
its
significance.
10)
for subsonic flow
6)
(b)
(i)
Derive
su
itable
expressions
for lift
and
drag
coefficients
of
a
flat
plate aufoil
at
small
angles
of
attack
using
hnearized supersomc
flow
theory
. (8) (ii) A
flat plate
of
1
01
x 0.2 m size is
kept
in
an
air stream
of
veloc
It
y 1800
kmph
at
an
angle
of
attack
of
5 degree.
Calcu
l
ate
the
lift
usmg supersomc
linear
theory.
Assume
that
the
static
pressure and temperature
of
the
free stream
air are
2 x 10
5
N/m
and
288 K respectively. (8) 15. (a)
i)
Describe
the transonic
flow
regime with
suitable
sketches of
flow
ii)
pattern
over a
two dimensional
airfoil. (6)
Explam
how
la
rge
drag
increase
takes
place
at
transonic
flow.
What
arc
the
control
measures
adopted
at
the design stage?
(6) (iIi)
What
are
the
flows
detrimental
effccts expcl lcnccd
in
sweep
back
~
00
b)
(i)
Write
a note
on
transonic
area
rule
.
(8) (ii)
Discuss
the
major
dIfferences
between Rayleigh
and Fanno
flows.(S)
3
53013

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