Wind Tunnel Measurements of The Unsteady Pressures in and Behind A Bomb Bay (Canberra)
Wind Tunnel Measurements of The Unsteady Pressures in and Behind A Bomb Bay (Canberra)
Wind Tunnel Measurements of The Unsteady Pressures in and Behind A Bomb Bay (Canberra)
CURRENT PAPERS
BY
J. E. Rossrter and A. G. Kurn
1965
PRICE 4s 6d NET
U.D.C. No. A.I.(@) E.E.Canberrs : 533.695.9 : 533.6.013.2 : 533.6.011.3!~
October, 1962
J. E. Rossiter
and
A. G. Kurn
!lhe unsteady pressures acting in and behind the bomb bay of a l/20 so,:
model of the Canberra aircraft have been measured in the 8 ft x 6 ft transonx
tunnel. The unsteady pressures are described by their r.m.s. values and by
amplitude and correlation frequency spectra. Time average values of the
pressures were also neasured.
The results show that the Canberra bomb bay is of the "shallrm type"
in which the airflow enters the bay and attaches to the roof before being
deflected cut by the rear bulkhead. Pressure fluctuations are most intenso
in the vicinity of the rear bulkhead and on the roof of the bay where the
flow attaches. Changing the Mach number from O-3 to O-6 has in general
little effect on the unsteady pressures (when expressed non-dimensionally)
but xwxeasing incidence up to ten degrees produces some decrease in thex-
magnitude.
2 TEST DETAILS 3
3 FfEsJL1s 4
L CSIKLUSIONS
4X'? 07 SfxBOLS
i,:;'? 03 Rl5XiZWCES
LIST OF ILLUSTMTIONS
FiJp
-2-
I INTRODUCTION
2 TEST DETAILS
Fig.1 is a general afiangement dramng of th'e model used for the wx.nd
+Jlnnel tests. The model 1s complete with fuselage, wings and tailplane but
the fin and pilot's cabin falring have been omitted. A smell block fitted
in the front of the bay represents an instrument tray which will be carried
during the flight-tests.
The model was supported frnm above, by a short stream-lined strut
attached to a sting which was held in the tunnel incidence mechanxsm
(see Fig.3). This method of support was chosen as being the least likely tc
affect the air flowing over the bomb bay, and the lower sde of the fuselz.gc.
The bomb bay has an inverted V-shaped roof, and both the roof and tl!e
lower fuselage line are swept up slightly towards the rear (see Flg.1). S'h,
doors retract partially into the bay when it 1s open. No attempt has been
made on the model to represen-< structural detatis such as mngs and strlngsx
The bay has a mean lengtudepth ratlo of approximately 8:l and a mean length;
tidth ratio of approximately 5~1.
2.2 Instrumentation
The model was tested over s, Mach number range from O-3 to 0.6 and, 311
order to facilitate comparison mth the forthcoming flight tests, the modct
incidence was adjusted at each speed to sxnulate flight at altitudes of
%CQ and 20,000 ft. Model vibration limlted the kinetx pressure at whit!,
the tunnel could be operated to 150 p.s.f. The corresponding unit Reynol?
number together with model incidences are given m the table below.
The time average and the r.m.s. of the pressures at each transducer
position were measured for 611 the test conditions. For M = O-3, a = 5*6”,
amplitude spectra mere measured at al.1 the transducer positions. Correla-tion
spectra were obtained for all transducers in the bay referred to transducer G
(Fig.2), and for the transducers behind the bay on the starboard side of the
fuselage referred to transducers J and N. In addition correlation spectra
between transducers at the ssme longitudinal station but on opposite sides
of the fuselage wers measured.
For the ether seven test conditions amplitude spectra were measured
for transducer p*sitlons F,G,H and N.
3 RESULTS
n+ I
-lL-
where p, is the r.m.s. of the pressure fluctuations within the bandudtn
of the analyser used to obtain the spectra
P(xi't) p(x,,t)
R... = - _ -
It will be appreclated that RIJ may be evaluated either for the pressw.:
fluctuatioss within the whole frequency range ?r fnr the pressure fluctuatlont,
within narrow frequency bands, in say. In the latter case, Rij 1s a fin&l .
of the rentre frequency, n, of the band and may be plotted as a "correlatlo:,
spectrum".
n 1 was cslculated. by fxst
qj( measuring the amplitude spectra of t+)s
instadcaneous sum au3 CiifYerence cf p(xi,t) and p(xj,t) then
(PC/q{+;, - (Pc/qJs);iff
Rij(d = .
4 (PLJqWx. (Pc/9J"),.
[ 1 J
-5-
indication of the size of the region over which disturbances retain their
identity - on the average. In addition, the variation of the correlation
coefficient along the direction in which the disturbances are travelling
will contain a measure of their average speed. In this connection it 1s
significant that for the special case of a pressure field which is entirely
periodic in character, the correlation coefficient is equal to the cosine
of the phase difference between the pressures at the twq measuring points.
Typically, the variation of Rij(n) along the direction of travel of dis-
turbances superficlslly resembles a damped cosine wave. The distances
between successive zero crossings may be interpreted loosely as ufd mea
wavelength of the disturbances and the rate of decrease in successive peak
values as a measure of the rate of decay of the disturbances.
Fig.6 shows the dis'crlbution of the mean pressures along the roof of
the bay and on the fuselage behind the bay for N = 0.3 and 0.6. The
pressure distrlbutlons at low incidence are typical of a shallow DJpe bay
In which the airflow enters the bay and attaches to the roof before being
deflected out by the rear bulkhead (see for example Ref.3). The pressure
rise associated with the flow attachment occurs at x/L + 0.45.
The curves for N = 0.3, a = 5160 and 10*4O show that increaging
incidence produces an appreciable reauctian in the magnitude of the
fluctuations within the bay, and. suggests that the,hlgher values of the
r.m.s. of the pressures measured at M = O-6 are probably mainly due to the
lower inciaences tested at this spe&. The effect of the inoidence change
on the pressures behind the bay ~WgXgible.
-6-
measured by Fail and others 4 m a Canberra type bay formed in a cy1indrico.L
fuselage. In Fig-y, the spectra for two points near the rear bulkhead are
compared with the earlier measurements. The agreement between the two se:r:
of results is reasonable bearing in mind the differences in the external
shapes of the models and the slightly different positions of the transducers.
Included In Fig.8 are spectra for M = 0.3, a = IO*&' for trio pcsxticns
in the bay and for two positions behind the bay. It can be seen that,although
as has already been noted,inc.reased incdence produces an appreciable decrease
in the magnitude of the unsteady pressures within the bay there 1s little
change in the shape of the spectra.
Selected correlation spectra for M = 0.3, a = 5.6' are shotm in Fig. il.
Within the bay (Fi&Il(a)) the main features cf a spectrum is a trough
followed at about ttice the frequency by a peak. The high values of the
c-x-relation at the peaks suggests that dzsturbances retain their identity
for qultt large distances as they travel along the roof of the bay. I& is
therefote possible to calculate the time average speed of propagation u, of
these disturbances. For, of it is assumed that tne frequency n' at which a
peak occurs, may be associated with a disturbance whose wavelength X', is
the seme as the distance between the measuring points, then
The mean value of G/U is O-57. It is not possible from the informat.on
available to calculate the speed of the airflnw just outside the bomb bay
YE'
but an idea of its magnitude can be estimated from the measured values of C
given in Fig.6 by assuming P
a L
u = (1-cp) .
C-7
-7-
This gives a value for U, meaned over the region of interest, of
Yd
0.73 so that -4% = O-78. That is, the mean propagation speed of dis-
turbances along the roof of the bay is about three quarters of the mean
stream velocity just outside the bay, which is of the same order as the
mean speed of disturbances in a turbulect boundary layer measured by
Tack and otherd.
Behind the bay, the pressures on the side of the fuselage are well
correlated in the region between the transducers at x/L = 1 *I5 and I.37
(Fig.ll(c)) but the pressures in this region are not well correlated titi
the pressures just behind the Es,r bulkhead (x/L = 1.05, Fig.ll(b)),
suggesting that there is a small region immediately behind the bay which
is isolated in behaviour from the main stream. Fig.ll(d) shows that
whereas immediately behind the bay (J ana K), in this smsll isolated
region, the pressures ere positively correlated in a cross plane, further
downstream the correlation is large but negative, suggesting that the wake
from the bay is unstable and moves from side to side of the fuselage.
4 CONCLUSIONS
(I) The Canberra bomb bay is of the "shallow type" in which the airflow
enters the bay and attaches to the roof before being deflected out by the
rear bulkhead.
(2) The pressure fluctuations are most intense in the vicinity of the
rear bulkhead and on the roof of the bay where the flow attaches.
(3) Changing Mach number from 0.3 to 0.6 has (in general) little effect
on the pressure fluctuations (when expressed non-dimensionally) but
increasing incidence up to ten degrees produces some decrease in their
magnitude.
(4) A study of the correlation spectra suggasts that disturbances travel
slang the reef of the bay at about three-quarters of the local airspeed
ext=ernsl to the bomb bay or at about one half of the free stream speed.
LIST OF SYMBOLS
pressure coefficient
cP
f frequency (c.p.s.)
P pressure (p.s.?.)
t time (seconds)
-a-
LIST OF SYI~OLS (Contd)
a wing lnoidence
E bandwidth ratio
x a wavelength (ft)
A bar - above a quantity has been used to udlcate Its tune avjrago
value.
LIST OF I;FFERENCES
-9-
SIMULATED
SECTION XX
/
INSTRUMENT TRAY
SECTION Y Y
(2X SCALES SHOWN)
L/; SECTION Z Z
t 6 6 6
.~&-&-&&+@ fi
-8 8 8 8
r L N P
DIMENSIONS GIVEN AS PROPORTION OF BAY LENGTH (= 13 35 INS MOOEL SCALE)
03 04 OS 06
M
01
FAN BLADE
FREQUENCY
0.05
I
Cb
0-c
0
0!.=.5.6~
d =10 4O
--+-- d = 2.20
-I 0 J
0 02 04 06 08 IO I2 I.4 1.6
XL I
I I I I I I
77 M = 0.3 d= S6O
A d = IO 4O
X M- 06 d = l.t"
+ d= t2O
dAi4 STARBOARD
(TRANS. J L N ANO P)
0 02 0.4 0.6 0.8 I.0 I.2 l-4 =eL I.6
PPP t PORT
(TRANS. K M 0 AN0 R)
01
0 I
0005
005 01 05 I n
0.05 0 I 05 I 7-L 5 IO 20
REAR ’
BULKHEAD HMC
.’
\I I _c /
0 01 i
o.oo5 \
0 01 0.05 0I 05 n 5 IO
(4 IN BAY
0 01 0.05 0 I 0.5 I n 5 IO
(b)
BEHIND BAY
0. I
0.01
I
0005
001 0.05 0 I 05 I n 5 IO 20
01
xL 5 I.26
005
ijF
I 05 I n 5 IO so
0 00s I I I I I I
< 01 005 01 05 I l-L 5 IO i
01
I I I I I I
00s 01 05 I n 5 IO 4
0.1
es I 26
00.5
i!$
0.01
OGO5
0 01 005 01 OS I n S IO 20
I \ Al/ \I\/-,
+ I.0
I--
F
-
, /
I.26
/ /
-1 o-
005 0-I OS I 5,lO 20
= (4
-I 0
005 01 OS I 5 * IO 20
+ I.0
= (4
=P,R
-10
00.5 0.1 05 I 5nlO 20
The unsteady ~resswes xtirg In and behind the bc;nb bay of a 1120
scale model of the Ca”berN aWWZft IZYC been nonswed In cne 8 it X 6 ft
transonic tunnel. The unsteady ~csswrzs a-e described by their r.m.s.
“al”es and by amplftude and rorrcl~rion frcqucncy spectra, Tine a”ErS@
values Of the p-esswes wcrc r1sc nea.sl!red.
The results show that tne Ccnbcrra bcnb bay is of the “shallow type”
In vmich the airflow! enters the bay and attaches to the roof before being
deflected o”t by the rear bulMxnd. FrfSSure f1”ctc~tion.s are nest intense
(over )
--
-+I.(@) E.E.CcnbwW :
533.695.9 :
1” the vlclnity of the i-car bulkhad and on the rmf c,f the bay irhere the
flow attaches. ChmelnC the Nxh nli~bw fro, 0.3 to 0.6 hm in Concral
little effect cn the u”stm,y ~rcss”rcs (when cx~rcssed no”-dinensiorally)
!,ut 1ncrcnsIn~ Incidcwe up t,, +,a, dq,mes ~rrod”cos scm (ICC~‘E~SCI” their
i aC”ltude,
C.P. No. 728
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