air force flight dynamics laboratory director of ...foreword thia report was prepared by m.e....
TRANSCRIPT
AFFDL-TM-73-120-FXG Tyffl'fr
AIR FORCE FLIGHT DYNAMICS LABORATORY
DIRECTOR OF LABORATORIES
AIR FORCE SYSTEMS COMMAND
WRIGHT PATTERSON AIR FORCE BASE OHIO
LOW MACH NUMBER TEMPERATURE MEASUREMENTS USING ENCAPSULATED LIQUID CRYSTALS
Max E. Hillsamer
August 1973
Project Nr. 1366
Approved for public release; distribution unlimited
High Speed Aero Performance Branch Flight Mechanics Division
Air Force Flight Dynamics Laboratory
Reproduced From Best Available Copy
AFFDL-TM-73-120-FXG
LOW MACH NUMBER TEMPERATURE MEASUREMENTS USING ENCAPSULATED LIQUID CRYSTALS
Max E. Hillaamer
August 1973
Project Nr. 1366
Approved for public release; distribution unlimited
High Speed Aero Performance Branch Flight Mechanics Division
Air Force Flight Dynamics Laboratory
FOREWORD
Thia report was prepared by M.E. Hillsamer of the High Speed
Aero Performance Branch, Air Force Flight Dynamics Laboratory,
Wright-Patterson Air Force Base, Ohio. The work was performed as
part of the AFFDL ln-house research under Task Hr. 136603 "Aerodynamic
Heating to Military Vehicles", Project Mr. 1366 "Aeroperfonance and
Aeroheatlng Technology", and covers work conducted between December
1972 and March 1973.
Models for the tests were designed and fabricated under the
direction of Mr. John E. Fehl, Aerospace Vehicle Branch (FXS), and
tests vere conducted by personnel from Aeromechanics Branch (FXM)
and Experimental Engineering Branch (FXN) of the Air Force Flight
Dynamics Laboratory. The author gratefully acknowledges their
cooperative assistance.
This report has been reviewed and is approved.
IlLlP P. ANTONATOS Chiei, Flight Mechanics Division Air Force Flight Dynamics Laboratory
11
",. .... 1.
ABSTRACT
An experimental program was conducted to evaluate the use of
encapsulated liquid crystals as a Beans of determining temperature
profiles in regions of interfering flows on wind tunnel models at
supersonic speeds. The tests were conducted on both plane surfaces
and on an ogive cylinder model equipped with 3 dimensional shock
generators at Mach numbers of 1.89 and 3.00 in the Trisonic Gasdynamic
Facility of the Air Force Flight Dynamics Laboratory. Freestream
Reynolds number were 1.0 and 3.0 million per foot.
Results show that models coated with encapsulated liquid slurry
and overcoated with a protective plastic film provided better
temperature profiles than models equipped with paper substrated
liquid crystals. Temperature profiles were easily discernible over :.# ' .V.'.."--
the entire surface of the ogive cylinder model within viewing range
of the camera, and specular reflections on the non-planar surfaces
did not invalidate any data*
'■''•;■ V-r .
•. ■ i ■* ■'
"'. '■•■{■*:''*■.';• ."••7 •
ill
:v.!'■-",'' -■:
'■*<?/• '•■: • '■\'?-'.''
CONTENTS
ABSTRACT PAGE
I. INTRODUCTION 7 1
II. APPARATUS
A. Models 3 B. Liquid Crystal Coatings 4 C. Wind Tunnel 6 D. Instrumentation 6
III» TEST DESCRIPTION
A. Test Conditions B. Test Procedure C. Data Reduction
IV» RESULTS
A» General B. Mach 1.89 Data C. Mach 3.00 Data
V. CONCLUSIONS
REFERENCES
LIST OF TABLES
TABLE
I. Test Conditions
II. Model Configurations Tested
iv
7 ,,=:. 7
- 8
;.''' '. •;• ''■' .
.'■;\. 9
10 H 16
■ y"„
•■:■
17
•V'.'
i::
'■'"■ .' :;^'
'■'■■ w: 'S '.' J ■ .-■•';
' ■.%'■•■•"
■• ^-.
■•;• ■-'.'-';r ;,V. : 1
ft -■'
: -.. .»''.' ■»
% ■ > '
'^' . , •■-'.. • -r '• .-.•■ . i ■ • .^ » - .. '^ <■ ' f . * -i* "
1 ** - - >A , " '
'."■ .* "<■■-. > .. ,' . %•■
...■ ' -;' "* *T'~' ...fiv *.i'. ■■/'
. .; . • •" ' *•' - ,
>'*>'.<■■
ILLUSTRATIONS
FIGURE
1« Sketches of Flat Plate MOdels
a. Model C with Fin A
b. Model A or B with Fin B
2. Ogive Cylinder Model D
3. Color-Temperature Variation of NCR Type W-15 Encapsulated Liquid Crystals
4. Facility Layout
5. Comparison of Paper and Slurry Mounting Methods for Encapsulated Liquid Crystals
a. Paper Mounting, No Fin
b. Slurry Mounting, No Fin
c. Paper Mounting, Fin A, Xy - 8 in., «p ■ 10 deg.
d. Slurry Mounting, Fin A, Xy - 8 in., 6p - 10 deg.
e. Paper Mounting, Fin A, Xy ■ * in., 6p - 10 deg.
f. Slurry Mounting, Fin A, Xy - 4 in., «p - 10 deg.
g. Paper Mounting, Fin A, Xj, - 0 in., «p - 10 deg»
h. Slurry Mounting, Fin A, Xj, - Oiin., 6p - 10 deg.
6. Comparison of Temperature Profiles for Paper and Slurry Coated Models
a. Paper Mounting, Fin A, Xy - 0 in., «p - 10 deg.
b. Slurry Mounting, Fin A, Xy • 0 in., «p - 10 deg.
7 Through \2» Temperature Distributions in the Interference Regions on Model C.
7. Fin A, Re. - 3.0xl06/ft ]f
«. X- 8 in., 8 - 15 deg« >
PAGE
20
20
21
,:23>:
24
2*
25
25
26
26
2?
27
29
28
f.
..»".
b. Xy • 4 in., «p • 15 deg. "tf - 30
• ■■* ■ • •>" I '■ .
FIGURE
8. Pin A, Re„ - 1.0xl06/£t
a. Xy - 8 in., «F - 15 deg.
6p - 15 deg. b. X- ■ 4 in.
e. Xy ■ 0 in.,
9. Pin B, Re, - 3.
a. Xy - 8 in.
b. Xy - 4 in.
10. Pin B, Re„ - 1.
a. Xp - 8 in.,
b. Xp - 4 in.,
c. Xp - 0 in.,
11. Pin A, Re„ - 1.
a. Xp " 4 in.,
V. Xp - 0 in.
12. Pin B, Re„ - 1.
a. Xp - 4 in.,
b. Xp - 0 in.
13. Temperature Profiles on Model D, Re. - 3.0x10 /ft, o • 0 deg. |
a. Pin A, 6 • 0 deg. *
b. Pin A, «p - 5 deg.
c. Pin A, «p ■ 10 deg.
d. Pin A, «| - 15 deg.
14. Temperature Profiles on Model D, Re. - 3.0x10 /ft, a *.12 deg.
6p - 15 deg.
Oxl66/ft
6p - 15 deg.
6p - 15 deg.
0xl06/ft
6p - 15 deg.
«P f3 15 deg.
«p - 15 deg.
0xl06/ft
6p fr 5 deg.
6 • 5 deg.
0xl06/ft
6-5 deg.
6p - 5 deg.
PACE
31
32
33
34
35
36
37
38
39
40
41
42"
«. Pin A, «p - 0 deg.
43
43
44
44 V
45
vi
FIGURE PAGE
46
46
b. Pin A, 6p ■ 5 deg. 45
c. Pin A, *p - 10 deg.
d* Pin A, *p • 15 deg.
15. Temperature Profiles on Model D, Ke„ 3.0x10 /ft, o ■ 0 deg.
a. Pin B, 6p - 0 deg. 47
b. Pin B, *F - 5 deg. 47
c. Pin B, «p - 10 deg. 48.
d. Fin B, 6p f 15 deg. 4«
16. Temperature Profile« on Model D, Re. -3.0x10 /ft, o ■ 12 deg.
a. Pin B, «p - 0 deg. - 49
b. Pin B, «p - 5 deg. 49
c. Pin B, 6p - 10 deg. 50
d*. Pin B, «p - 15 deg. ; 59
17. Temperature Profiles on Model C, M. • 3.0, Fin A, 51 Re. - 3.0xl0ö/ft., Xy - 0 in., «p - 15 deg.
18. Temperature Profiles on Model D, M. • 3.0, Re. ■ 3.0x10 /ft, ■ o • 0 deg. ' ' 'f-f.-. I . •/
a. Fin A, «- f 0 deg. ' , 52
b. Fin A, «p - 10 deg. v 52
19. Temperature Profiles on Model D, M. - 3.0x10 /ft.,'.,'- o • 15 deg.
a. Fin A, 6p - 0 deg.
b. Fin A, «p - 10 deg.
- ■.-->
viii
^■i53U>
■ "; 5*S-:
- "•'■'v: ■ ■■■'''£
'.'■':.■ ' ."' ''*.
Symbol
M
r
T
X
ac
6
y
LIST OP SYMBOLS
Description*
Mach mmber, dimensionless
Reynolds number, 1/ft
Recovery factor
Temperature, deg F or deg R
Axial distance measured from model leading edge» in.
Angle of attack, deg.
Fin or canard deflection angle, deg.
Ratio of specific heats
Wavelength of light, nm.
Subscripts
AW
F
0
V
00
Adiabatic Wall Conditions
Fin or canard
Total or stagnation conditions
Model wall conditions
FreeBtream conditions
-*'
> .»'.v.
,•-■" i ■ v-.Y *•■■ :'.*?*:'J" "'T';
: ■■. ^ '>' -.•'.
viii -.AV .v-
■ -**'■'."■■ - ■■*"•* o
•■'■ &•:■.'-•.■*>'■■
•ÜV ■;■-.•
I. INTRODUCTION
Aerodynamic heating of aircraft and missile configurations in
the supersonic flight regime, while not so severe as to cause
catastrophic failure, can'result in degradation of the structure.
Of special interest are regions around wing-body or fin-body
junctions where localised "hot spots'* develop because of intersec-
ting flow fields*
The purpose of the present study was to investigate and evaluate
Methods of obtaining aodel surface teaperatures and heat transfer
rates in regions of.interfering flow fields at low Mach numbers*
Several methods have been used in wind tunnels to measure temperatures
and heating rates in regions of interfering flow fields at Mach numbers
of 6 and above. Neumann and Burke (Reference 1) compare results
obtained by them and others in interfering flow fields of 2 and 3-
dimensional shock generator models. Models used were thin skin flat
plates equipped with standard thermocouple instrumentation* Incomplete
mapping of high heating regions resulted because of lack'of adequate
Instrumentation in areas of interest. Thin skin thermocouple instru-
mented models are also quite costly to build.
Various investigators such as Jones and Hunt (Reference 2) and
Patterson (Reference 3) have used a method of obtaining quantitative
heat transfer measurements with temperature sensitive phase change
coatings applied to models made of low conductivity materials, such as
Teflon or Stycast. Schulte (Reference 4) used this phase change ,
•'".■"■'■ -.-■."...;■• .. ■• ■'.".-- , ". ■* ■ -'-\ '*'- . ■', / :. *'■ ' ';.;
■ ■ ■■. .:■••■••;, it:: ': ■ ■* ■ *: ..■,:■:/,:■.■: ;.;• ■ . - ,. .-■■■.-•• . . ■■ ■ •{:;■ «■-.•»*■ T..: - .•';..-• .-
■■ ; ■..•■.:.•••.-.. ■■..."■ . • . ; ■ (f-.■ -i---*-. ■♦ • • . ■' •„., . /: ... ■■ ■ '■■■■ ; ■ •' •; ':\ W^v?.; • ; .
": ' • ''. i» '..'.•.. ■.'•. •' ' '■ .'■ ■'' *i'- ■'*■ '■' '• •. ■ i ■
coating method to quantitatively obtain heat transfer rates in inter-
ferfering flow regions on a flat plate model in the AFFDL High Temperature
Facility at Mach 10.
An obvious disadvantage in the use of the phase change coating
technique is that the phase change is not reversible. Model surfaces
must be cleaned and coated before each test run. Also, the Stycast
castable model material used for the model fabrication is not completely
homogeneous, and thermal properties of the material vary from batch
to batch.
McElderry (References 5 and 6) conducted boundary layer transition
studies at supersonic speeds using cholesteric liquid crystals attached
to plexiglass models. The start of transition was determined by the
color change of the liquid crystals due to increases in model surface
temperatures. Klein (References 7 and 8) was probably the first
investigator to report on the use of liquid crystals for aerodynamic
testing.
While the investigations of McElderry and Klein were mainly concerned
with locating boundary layer transition and turbulent regions, the liquid
crystals technique appeared applicable to complete thermal mapping of
models, with special emphasis on regions of interfering flow fields.
Advantages of this method are that model fabrication costs can be low,
complete temperature profiles can be obtained, color changes of the
liquid crystals are reversible, and the liquid crystals are obtainable
over a wide range of lower temperatures suitable for supersonic wind
tunnel facilities.
The present studies evaluated methods of attaching liquid crystals to
the models, placement of light sources and cameras, mechanical stresses
on the coatings and thermal mapping of the models* No means was
available for obtaining temperature-time variations on the models, so
transient heat transfer values were not obtained.
II. APPARATUS
a. Models
Four plexiglass models were constructed for use in this study.
Plexiglass was chosen for its low thermal conductivity, uniformity of
material, and ease of machining.
Two models, identical in size and shape, were used to evaluate methods
of attaching liquid crystals. The models were flat plates 8 in. wide,
16 in. long and 3/4 in. thick with sharp leading edges of 15 deg bevel.
The top surface of the first model was recessed approximately 0.014 In.
from 0.250 in. back of the leading edge to the rear of the model. This
recess was provided for mounting plastic covered, paper backed sheets of
liquid crystals with two-aided masking tape. A smooth model surface was
thereby achieved. The top surface of the second model was not recessed
and was painted flat black to provide a dark base for the liquid crystals
slurry an alternative to the paper backed sheets previously used.
The third model tested was a flat plate identical to the second
model except that the width was 14 in. Use of the wider mod^l assured
that flow disturbances from the front corners of the model would npf
affect the flow in the region of shock generation.
Two shock generators were used with the flat plate models. Each
generator was 7 3/4 in. long, 2 in. high and 1 3/8 in. wide with flb^rp
leading edges of 20 deg bevel. The leading edge sweep angle of the first
•v ..,-■..'
' 1-~X~y •i '>
■:.'.•*••-•■'
was 0 deg and 30 deg on the second. Holes drilled through the flat
plates permitted the shock generators to be bolted on at any desired
position. The shock generators were aluminum painted flat black to •
reduce glare* from Camera lights.
To evaluate the use of liquid crystals on non-planar surfaces,
an ogive cylinder model, 12 in. long and 3 1/4 in. base diameter was
fabricated from plexiglass and painted flat black. Two different size
canards were supplied for shock generation on the body of the model. ;
Both canards had a leading edge radius of 0.016 in. and a leading edge
sweep angle of 57 deg with'a trailing edge sweep angle of 10 deg.
The larger canard (A) had a base chord of 3.73 in. and a span of 2.62
in., and the smaller canard (B) had a base chord of 1.90 in. and a
span of 1.36 in. The canards were equipped with roll pins which were
inserted into a hole in the side of the model 2.57 in. forward of the
base and held in place with a set screw. Canard angle with respect
to the model could thereby be adjusted.
Figure 1 is a sketch of the flat plate models with shock generators.
Figure 2 presents the ogive cylinder model with control canards attached*
B. Liquid Crystal Coatings .
Cholesteric liquid crystals are chemically cholesterol esters
mostly of fatty acids. These nonflammable substances are liquid in
mobility but crystalline in optical properties. When illuminated with
unpolarized white light, incident at a given angle, only one light
wavelength is reflected at each viewing angle. Small temperature changes
cause a shift in the molecular structure of the liquid crystals, and
light of a different wavelength is then reflected. Fergason (Reference
9) presents more complete documentation on the properties and character-
istics of the liquid crystals.
By selectively mixing liquid crystal substances color changes
through the entire visible spectrum can be obtained with increase in
temperature. The temperature span of color changes can be as small as
1.8°F or as large as 90*F. Temperatures can be measured with better than
0.18'F accuracy, and reaction time of the liquid crystals to temperature
change is less than 0.2 sec. Temperatures at which known liquid crystals
operate range from -4°F to 480°F. The color changes of the liquid crystals
are reversible, and the substances can be cycled through their temperature
ranges, any number of times.
Liquid crystals in their raw form are responsive to mechanical stress,
electromagnetic radiation and chemical vapors in addition to temperature.
The National Cash Register Company (NCR) has an encapsulation process ;
whereby microscopic amounts of liquid crystal compounds are encased, :fn
hard spherical shells id to 30 microns in diameter. ;; f
The encapsulated liquid crystals are more stable and less responsive
to mechanical stress or chemical vapors.
Encapsulated liquid crystals are available from NCR in either
sheet or slurry form. The sheets are made by sandwiching a thin layer
of encapsulated liquid crystals between a top sheet of clear plastic
and a back of black paper. The sheets are fastened to the model surface; - .'' "' . . "-■"•- '''■ ">■ '? ,
with two-sided masking tape. This method was used on the first model
tested in the present study» %1-Y £;^<:
'■'. 't:'" >' ;- ''"''■■1A . *•"-,
.'■■-; 3"*V ;'c 't ■-*:*-■ ' -■'
Encapsulated liquid crystals in the slurry form were sprayed
on the surface of the model with an artist's air brush. After the
slurry dried a protective coating of Krylon plastic was applied to
the model surface. A hard, smooth model surface was obtained with a
total coating thickness, including flat black paint, liquid crystals
and Krylon coating, of 1.1 mil. This method of application was used
on one 8 in. wide flat plate and 14 in. wide flat plate and the
ogive cylinder model. All models were coated with NCR type W-15 encapsu-
lated liquid crystals, which has a temperature span of 10.8 deg F from
start of red to start of blue color change* Figure 3 shows the range
and color change temperatures of this particular compound.
C. Wind Tunnel '
In-house testing was conducted in the AFFDL Two^Foot Trisonic
Gasdynamics Facility (TGF). This facility is a closed circuit, variable ;
density, continuous flow wind tunnel using air as the working fluid.
A variation in Mach number from subsonic to Mach 3.0 is provided through
the use of fixed two-dimensional planar nozzle blocks. :,:
Stagnation pressure and temperature can be set by the operator jrad
are automatically controlled to within +1 psf and +1°F respectively. [
Figure 4 is a sketch of the general layout of the wind tunnel. j^
Reference 10 describes the facility and associated equipment in full '
detail. ''[■:■''J^-.'S
D. Instrumentation , ■ * i:
Color photographs of the model at each attitude constituted th«
entire model data acquisition. A 4 x 5 graphic view caaera was pl*c*d,.\' >?• ■- v ■-• •-,
directly normal to the model surface approximately 6 feet fro» the -
V
subject. The light sources were two 500 watt, 3200 kelvin lamps about
30 degrees on each side of, and slightly higher than the camera. Four
second exposures at F22 were made on type L Ektacolor film.
III. TEST DESCRIPTION
A. Test Conditions
Tests to compare paper mounted encapsulated liquid crystals (ELC)
with slurry coated models were conducted at Mach 1.89 and a freestrearn
Reynolds number about 3 million per foot. Stagnation pressure was
1600 psfa, and stagnation temperature was varied from 100 to 115°F in
5* increments. The two 8 inch wide by 16 inch long flat plates were
used during this phase of the test.
The 14 in. wide by 16 in. long flat plate and the ogive cylinder i •
were tested at Mach numbers of 1.89 and 3.00 and freestrearn Reynolds
numbers about one and three million per foot. Table I lists test
conditions for each model.
B. Test Procedure \
All models were provided; with ELC coatings several days before start
v ■ of the tests and stored so;that testing would not be delayed by model
preparation. No deterioration in coatings was evident because of
storage. \
Prior to starting the wipd tunnel for each test run, each flat plate /
model was rolled so the coated surface was in the horizontal plane. i
After starting the tunnel, 'the model was rolled 90 deg with the coated
V surface toward the camera. ) This starting procedure reduced the danger of
the model damaging the windows in case high starting loads would cause
!
y ' . '.- " : ■■'■.-
the model to break loose.
First test point pictures were taken at the maximum required stagna-
tion pressure and minimum stagnation temperature. The temperature was then
increased with photographs obtained every 5 deg. Stagnation pressure and
temperature were then reduced to minimum required conditions and the
procedure was repeated.
Shock generator fins were tested at the most rearward locations first
so that the shock generators would cover the mounting holes in the surface
of the model on succeeding runs. During Mach 3 testing the mounting holes
toward the front of the flat plate were filled with modelling clay to
assure a smooth surface ahead of the shock generator.
The ogive cylinder model, D, was installed with the fin mounting
hole toward the camera. Initial test point for each run were at maximum
stagnation pressure and minimum stagnation temperature. The model was
pitched from 0 deg to 12 deg with test photos being obtained every 4 deg.
Stagnation temperature was then increased and the angle-of-attack sequence
was repeated.
Table II is a summary of model configurations used during testing
\ ■ •
in the 2 Ft TGF.
C. Data Reduction
There was no method available for removing the model from the tunnel
airflow' and providing a time base to obtain transient heat transfer rates.
Therefore, all data presented in this report are in the form of temperature
distance lines or isothermal line patterns in the region of the shock
8
generators. These Isothermal lines were obtained fron 8 x 10 in. color
prints of the test photographs taken at each test point.
The standard 2 Ft TCP data reduction was used to provide stagnation
and freestream operating conditions in the wind tunnel.
IV. RESULTS
A. General
Data presented in this report are from two separate test periods in
the 2 Ft TGF. The majority of test time was concentrated in the Mach
1.89 studies, with only sufficient runs at Mach 3.00 to determine the
suitability of the method. Results presented in this report are at a
stagnation temperature of 100*F for Mach 1.89 and 115*F at Mach 3.00.
The higher temperature was necessary to produce color change profiles
at Mach ?.0.
A total of 392 color photographs of model temperature profiles were
obtained during this test. Because of the time Involved in reducing
data from all the photographs, only representative temperature profiles
are presented. Reproduction of color photographs is quite costly, so
only representative color prints are presented in this report. Sufficient
fine detail was not obtainable from black-and-white prints of the color
negatives. Temperature profiles presented were obtained by plotting distances
measured from color photographs. None of the data were reduced to heat
transfer coefficients because no adequate time base was available to
determine heating rates.
B. Mach 1.89 Data
The first phase of this study consisted of determining the most
suitable method of attaching liquid crystals to the flat plate models.
Comparisons of the paper and slurry type mounting methods are presented
in figure 5 (a-h). For identical fin locations, high temperature areas
are the same on both models. However, much clearer detail is evident on
the slurry coated model because of the smoother test surface. The
paper backed ELC appeared to bubble and wrinkle when exposed to the
tunnel airflow causing tripping of the model boundary layer. Streaks of
color on the paper coated model are evidences of this boundary layer
tripping. With the fin at its most forward location (fig. 5 g)
the entire rear section of paper mounted ELC came off during testing.
Klein (Reference 7) utilized raw (not encapsulated) liquid crystals
in the slurry state which were free-flowing during wind tunnel operation.
The coating tended to leave regions of high shear, and necessitated
recoating the model after a period of testing. His recommendation was to
cover the liquid crystals with a thin transparent plastic coating which
would shield the crystals from mechanical stresses. The slurry coated models
used in the present study were coated with Krylon plastic spray over the ELC.
This method provided a hard model surface which showed no airflow shear
effects. Although reflections from the light sources are evident, color
changes due to temperature were visible in color photographs over the
entire model surface.
10
The rough appearance of the model surface in figure 5 (b,d,f and h) was
caused by the method of Krylon spraying used, and the model boundary layer
was not affected in any way.
A representative comparison of the temperature profiles obtained from
the two types of model coatings is shown in figure 6. While the patterns
are generally the same on both models, the line of constant temperature are
much clearer on the slurry coated model (fig. 6 b). Broken and nonuniform
color patterns on figure 6a were caused by the paper mounting separating
from the model as mentioned-previously. Clearly defined regions on the
slurry coated model (figure 6 b) show the bow shock from the fin and a
high temperature, region between the bow shock and the fin.
Figures 7 through 10 present temperature profiles on the 1A x 16 in.
flat plate (model C ) with the shock generator fins at a deflection angle of
15 deg. Color photographs from which the temperature profiles were derived
show boundary layer tripping occuring at the higher Reynolds number. This
tripping was the result of leading edge surface irregularities caused by
slight mismatches between the stainless steel leading edge and the plexi-
glass test surface.
Bow shock angles from the shock generator fin are shown in the tem-
perature profiles of figures 8 through 10 and are greater than the 48 deg.
Shock angle predicted for a 15 deg wedge in Reference 11. The higher shock
angles shown on the profiles were caused by the shock generator fin being
behind the bow shock from the basic model. Two different flow fields, one
from the flat plate and the other from the shock generator fin, intersect
to form the flow field producing the temperature profiles« These figures
show that as the fin is moved forward, the initial shock angle decreases
until at X - 0 in., the shock angle is about 50 deg. The initial shock F
angle from the fin is also greater for the lower Reynolds number case.
A comparison of figures 7 and 9 showed that the shock angle was approxi-
mately 3 deg. less for the 20 deg. swept fin (B) than for the 0 deg.
swept fin (A).
Secondary areas of high temperature are shown close to the fin/plate
junction. While no oil flow or surface pressure data are available for
these flow conditions on the model, the flow field appears to compare with
that discussed in Reference A, Section IV. A conical corner flow region
starts at the plate/fin junction, and vortices emanating from the corner
vertex produces regions of separation and reattachment with higher tempera-
tures evident in the reattached regions.
Temperature profiles in the interference region of the model with
the fins at 5 deg. deflection are presented in figures 11 and 12 for a
Reynolds number of 1.0 million per foot. Predictions from Reference 11
for a 5 deg. wedge show an undisturbed shock angle of about 36.5 deg.
Profiles of figures 11 and 12 indicate a minimum shock angle of about
28 deg. for the 20 deg. swept fin (figure 12b) to 37 deg, for the 0
deg. swept fin (figure 11a). As in the profiles for fin deflection angles
of 15 deg., the profiles in figures 11 and 12 show secondary areas of
high temperature between the fin and bow shock»
Results of using encapsulated liquid crystals on a non-planar sur-
face are demonstrated in the temperature profiles of figures 13 through 16.
Reference 7 indicated difficulties in obtaining acceptable results with
12 . " ^i.%':i: &:?\
11
M i :
r • i ' ! i I. 1
liquid crystals because of specular reflections and adverse angles of *
illumination and viewing. On planar models these problems can be resolved
by using a single light source and camera placed normal to the model sur-
face. However, on curved surfaces light source and camera placement must
be compromised by trial and error. Profiles on the ogive cylinder model
presented in figure 13 through 16 indicate very good resolution of fin in-
duced separation and high shear regions can be obtained on bodies of rev-
/ olution equipped with control'canards.
/ • . ■
Generally, the temperature patterns are quite similar for all canard
deflection angles and model/angles of attack. A high temperature region
i is seen in the location of the canard bow shock. A second high temperature
region extends along the canard in a region of high shear. Between the two
high temperature areas is a low temperature secondary separation region.
Although no oil flow data Ware obtained, temperature profiles indicate flow
characteristics similar to /those formed on the flat plate models and results
at higher Mach numbers suclWas presented in References 4 and 12.
The base geometry of jcanards A and B was contoured to match the surface
of the ogive cylinder wi^h a canard deflection angle of 0 deg. As the
;/ ■■■■• :-':
canards were deflected* to 15 deg., a gap appeared between the front'-point
of the canard and the Model body. This gap was unavoidable and is espe-
cially apparent in figures 13 and 14. At a canard deflection of 0 deg.,
the color change star\ is 0.10 to 0.20 in. behind the front of canard A.
Small disturbances in temperature profile occvring about the 9.25 in.
station were caused by thexroll pin used to fasten the canard to tue node!. ■ ■ ■ \ '-":•-•.:•'■
■ ,: ■*: >.-::■ ■ .■■:';- r&Hi -■' '
k 13
C. Mach 3.00 Data
A very abbreviated test program was conducted in the 2 ft TGF at
Mach 3.00 to determine the sutiability of the models and test procedures
at higher Mach number. Maximum stagnation temperature in the TGF was
limited to 115-F by mechanical constraints. The adiabatic wall temperature
was calculated by the equation
TAW"
'l+(^)rM 2
K^K _ To
where r - 0.85 for laminar flow and 0.89 for turbulent flow. For Mach 3
flow at a stagnation temperature of 115*F the adiabatic wall temperatures
were calculated as 59.8'F for laminar flow and 74.4#F for turbulent flow.
While the color change range of the ELC was suitable for Mach 1.89 testing,
model surface temperatures at Mach 3 were suspected of being too low to
produce color change profiles of an acceptable quality. Representative
results of Mach 3 testing, presented in figures 17 through 19, show that
good temperature profiles were obtained in the interference regions of
the models. \
Figure 17 shows temperature profiles on the flat plate model C with
fin A at the most forward position and deflected 15 degrees. At Mach 3
there were no evidences of leading edge imperfections causing tripping of
the model boundary layer as was observed at Mach 1.89. The fin bow shock
angle shown in this figure is approximately 43 deg. Reference 11 predicts
14
a shock angle of 32.2 dcg for a 15 deg wedge at Mach 3.0. The greater
measured than predicted shock angle was caused by the flow fields from the
model and fin intersecting to form a flow field similar to the one discussed
in Reference 4, Section IV and earlier in this report. Also shown in this
figure are a low temperature separated region and a high temperature, high
shear region close to the fin.
Figures 18 and 19 present temperature profiles on model D with canard
A. Profiles produced on the non-planar model at Mach 3.0 are quite similar
to the Mach 1.89 data. The most notable difference is the Mach 3.0 inter-
ference regions are narrower than those on Mach 1.89 data. This is due to
the lesser canard shock angle at the higher Mach number. The high tempera-
ture, high shear region and the low temperature separation area are evident
in figures 18 and 19...
I
15
I
i
V. CONCLUSIONS
The use of encapsulated liquid crystals was shown in Reference 5 to
produce better results than raw liquid crystal for temperature measure-
ments on planar models. While Reference>5 presented results of using
paper mounted ELC, the present study shows the ELC in slurry form, s
sprayed on and oversprayed with a protective plastic coating was the
most suitable method of using liquid crystals for aerodynamic testing.
No adverse effects from mechanical stresses were noted, and color patterns
were not obscurred by specular reflections.
Use of encapsulated liquid crystals on non-planar surfaces was demon-
strated in this study. Temperature profiles were easily discernible over
the whole viewing range of the camera, and high temperature regions were
obtained on the surface of the ogive cylinder model greater than 75 deg j
■•» , .■■■'.■'('
from normal camera viewing line. j
f The addition of a technique for cooling and shüding the model from j
the alrstream plus a fast model injection system with time base would pro- \ " ■ ■ • I
vide a means of obtaining transient heating rates using liquid crystal !
coatings. High speed movie photography would be necessary to observe the
formation of color patterns on the model.
Results of the present study have shown that encapsulated liquid j j
crystals provide a useful tool in determining flow patterns and regions i
of high temperatures on models in supersonic flows. This method will be f
used in future tests to determine high heating areas on weapons systems
externally stored on the underside of an aircraft wing at supersonic speed«.
More complete mapping of the high heating regions can be accomplished by
this technique than with thermocouples on thin skin models. U% f
16
i
i. ■E
n ',;-:%± :"?U ■ ' *" **■■&-
-r-: .-!_■ '■'j-■>■'■'-' ;.- P
''■£&■■ ' ■' '- ''' .'(
-* '?*?>■ ■■,, v ■ *.
}
* '■. r>... '•??-' --- ■; *. ' ,- '; ■
;,, £• - *.-
.': -<B.<» .-. /■/
REFERENCES
1. Neumann, R.D. and Burke, G.L. "The influence of Shock Wave-Boundary Layer Effects on the Design of Hypersonic Aircraft?, AFFDL TR 68-152, Mar 1969
2. Jones, R.A. and Hunt, J.L. "Use of Fusible Temperature Indicators for Obtaining Quantitative Aerodynamic Heat-Transfer Data", NASA TR R-230, Feb 1966
3. Patterson, Jerold L. "Heat Transfer Testing in the AFFDL High Temperature Facility Using the Phase Change Coating Technique", FXG TM 70-12, Aug 1970
4. Schultz, H.D. "Experimental and Analytical Investigation of Temperature Sensitive Paints", AFFDL-TR-72-52, June 1972
5. McElderry, E.D. "Boundary Layer Transition at Supersonic Speeds Measured by Liquid Crystals", FDMG TM 70-3, June 1970
6. McElderry, E.D. "Boundary Layer Transition Mapping at Supersonic Speeds Measured by Liquid Crystals", AFFDL-TM-73-5-FXG, January 1973
7. Klein, E.J. " Application of Liquid Crystals to Boundary Layer Flow Visualization", AIAA 3rd Aerodyanmic Testing Conference, AIAA Paper 68-376, April 1968
8. Klein, E.J. "Liquid Crystals in Aerodynamic Testing", Astronautics & Astronautics, Vol. 6 Nr. 7 July 1968, pp 70-73
9. Fergason, J.L , "Liquid Crystals", Scientific American, 211 (2), August 1964
10. Allen, N.H., "The Two-Foot Supersonic Gasdynamics Facility", AFFDL/FXM, 1 August 1968
11. Ames Research Staff, "Equations, Tables, and Charts for Compressible Flow", NACA Report 1135, 1953
12. Bramlette, T. Taz, "Flow Field, Pressure and Heat Transfer Associated with Small Fins in Laminar Hypersonic Flow", SCL-RR-720339, )r November 1972 V: ";« &'-:1;
I t. f ■•;
17 <.%r. ■ r ".'
r :'. '' ■ -y.".:' :
■ ..; v ,-• '" .. "•
•j.--..'r>::-'- ;;}. ?:■ ■ '■ ■* .
<<;v
Table I, Test Conditions
Model Mach Nx • Re. X106/£t Po, PSFA To, °F
A, 8" x 16" Paper Coated
1.89
i
3.0 1600 100— 115
B, 8" x 16" Slurry Coated
1.89 \ \
t \ i /
3.0 1600 100 — 115
C, 14" x 16" 1.89. /
\
3.0 1.0
1600 560
100— 115 100 —115
D, Ogive Cylinder 1.89 (
3.0 1.0
1600 560
100—115 100 —115
C, 14" x 16" 3.00
/
' 3.0 1.0
2900 1000
110, 115 110, 115
D, Ogive Cylinder 3.0 / 3.0 1.0
2900 1000
115 115
;
\
? v,
l
18
^^■^■^^^i^^^
Table II, Model Configurations Tested
Mach Mr. X106/ft
Model Fin X, in. 6 deg a deg
1.89 3.0 A (8 x 16) A 0,4,8, off 10 0
1.89 3.0 B (8 x 16) A 0,4,8, off 10 0
1.89 1.0 & 3.0 C (14 x 16.) A & B 0 4 8 off
5,15 0.5.15 0.5,10,15
0
1.89 1.0 & 3.0 D (ogive-cyl) A & B 0,5,10,15 0,4,8,12
3.00 1.0 & 3.0 C (14 x 16) A off, 0,4,8 5,15
3.00 1.0 & 3.0 D (ogive-cyl) A & B 0,10 0,5,10,15
19
a. Model C with Fin A
b. Model A or B with Fin B Figure I. Sketches of Flat Plate Modele
j2fL
o
I
cO
21
110 r
100
90
J H* 80
70 -
60 400
From Edmund Scientific Co. Bulletin Nr. 7II3I7-I
■B R 500 600
X.nm 700
Figure .3. Cobr-Temperature Variation for NCR type W-15 Encapsulated Liquid Crystals .>• .1.:
22 r&.i-
u
«0 c
o O
(J
O (9 'C t-
Q U. U. <
0) L. D
Ü
23
■..yj'i'nyri!. FT »vm-aS-WÜ «Al'BWU^.- - J,.1..- ,>l""Jg/ r^T.T ^.T'^iFA'f/
Paper Mounting, No Fin
Slurry Mounting, No Fii
arison of Paper and Slurry Mo UP. oes for Encapsulated Lieuid Crv
d. Siurrv Mountir.a, Fir. A, X =8in., : =10 dec F F
:ure 3 (Continued)
v =ii -i
g. Paper Mounting, Fin A, X =0in., 6 =10 deg, F F
Figure 5. (Concluded)
27
iiMi|ii|im»iiwimimiiiiiiiHintfiiimniimmiwiimi iMMifH if §•#*§»§•■■■»■■■»■ ■■■■■■■ i ■»■r*-»r*» "*«■■■■■*:■*-w»r* ■»■* ■«■rwn i !•*«■§«« ~*«.itif*< ta*««§r=sv**m«> ■■■■■*• ■ ■• ■
a■•■■■■*■•■■■■■ >■«■■■■*•
ffö^ig it^tttCftxttL ̂ ^^^A:toj|||[|||i|;[|[lllllllllllil llftjftttfflffi MfflMM» M ffi m: 111: 111 §1
• \{■ -j44+ 11 j j j! j i | i| ■ { j I j!! |- j i j | 1 h 11 [1111 milli 11 1jlji
"V1 liilJilMlJlllti it'll 1114444-14444-111111 IrHTTJ-J^ll-^-fHT'^i ::S:
MM ITTTTT ' BlMB^i:^|ii. -i4-~ -i-i+4- 1)11 11 iT] j i f I ) | [) 11 j 444j-rH-rm) i! 1 i i i 11II1 j 1!! 11 j i 11111 iTttl"
JI±J: tuU-fi+'iit it.rt:ttki±t±±; 5t|-tttr±4tt 44-j-Hi4n It rfirfirn I'll rf T1T t'TI "H~H" n'ff"'|TT::
[ | j [ | [j-f-j HI (11111444411111 tri 1 j ij | HI IH j-) t M j 1 it 1 HT" i + 4+' -4-- ■
■4-1 |l 4M » -f-'t— T*
4iJ4:±^4^ 4444txl
§i:jf|g||j 4- - - +1 - | | j | ) | j | illllllilllllllNllllllillliy^
iffiTm "Tnii iHrlüiifitlitf
l|S&HJ|i 'til 111111II111 HI'MMI H1M1111111111 111 111 Tl 111 ttlT tt -ffl** 444--'T£"
1 1 j j till V i\
itt ttii ± if: I
jfgggjfjj||a [J1 TTIJ 1 ri \ 1 T 5 iin": 5£: ^^^" '
ElffiffigH ^llllltiJirHllllllllllllllll^lllllfllllmH F'ITT^^HS 11 lTrUTulXrl.11 r r Li 111111111 tl 1 111 111 if 111 1 1 IHT H' V 4r+r-K^r4'
f-ffifflffi 11 In rfhf-1111 [ItlT il fl ^^^^ttS:^+S^S
:'§|^ili j§iliillll;illililllllllllilllllllm^^ 1 flUlJ mil rrk \ IWIH-H Iml w ftliia nffttiTtfr-INI ■ rTr'TFi ^ !g*S 1 Uli IHIII 11II II III in rTLritlrTlJiH I I IT TT ■ TTTF ""Sf^FiSS 1 jiti i±j-i J:S3 1111111111111111[11111111111Inrflrm U ifn , itpt
-11 f-t- j-f-j4 • 4-t i ■ T
4444- 4444- -444- -H
-A H rMS}3SP :::U'LTI4- n'JI
;;|;ME| 1 11111 11111111111111 MJtijjjj- S - -J-J-H- :P^i:vPt
llllil 11111 111 11 1 1 i H :ffi^^
Til Till 1 Tl MTH I 11 i 111 1 1 Tl i Ml 1 111 11 ill 1111II1 -^-" T!I4- JA-^t^fir^c
-lü; trfffc;;S ̂ jgfpJitjft llllllllllllllllll lllllllllllil^ jtü-±^tej:±
^" i" "fn"t" TfT
„[, tli 4 {4-L 4-4--t- 1111 |4-j-j- - III} 11111111 H"H*H*H MM H H H II111111II1 j 1111 titi
^plmi .^tiT itii Kit'i lot ml -JTIT it t ii + JnSxrii
J 11 111 || lllllllllllil llllil llHfHjfm
mi$f®| f:||||§| 11 n nTnTi 'I'TTi'i 11111111 1 rt 111111 I i ill I tl 111111 IT +r ■ - ■TT4= 44-u 4444+
32 ilF; rtfltt i {iir£?rÜ &- -j-r44- "j rr| xBx ffj U1'.H*" 1111111 i 1111 j j 11 |"I11111111111LUJJI1111111111111
■itrnw-f-i min f«|: 111 111 111 Im 1 H Ir HPT* •rftr rftT TTrtfrt t. fl+j: jj-[-j- i±j± TTltl ft ml lllll TIT 1 ~t~ti■ 1'M11C1' i,!l 4-tif 4-t44--H
J^JSt-Mt-H i- -1+H- -' i 11 -m-f 1111111 irniiTii 1 iniiTiin 1111111111111111 \\* 111 H P' 11'^!
j* ■. ...4' ■■ * * * -*-1
J. . iiil lul 4-i-ti-
Sfl5t|'3]|s fi||il| jjlllllll lllljllll llllil W ^[ftfHl^ ̂ tl^lii
ü -U+f +!-rt- tt; ;ffl-ttt||i'fflj'l'titN 111 Uli 1 iTTnTi 11 \\\\\\f trftTTTTTT^THuT^t—ff
iaMSSIg t; rtfi tnt "HlT i j 1111| j-j !■ || Hi HU I-1-I-I4-1IM ill II11 i 1-11 1 P1 11 i | -fji *^l4- -fJ4-|-fi-UX
jjjpi \m #111111 IH IHT IliiHTTTI liTTiTrn]l iitTiTTTTTl 1 ntTn"TttT i.nrHftT
^ÜHl
^-•r-rtf^tttttt'll^' "I'l'iii +tl!|li|| itt++tttttttHttttttTti"ttlt iiitia»«iitii*iiia*M ••••■•••■•■■»*■■ aM"**laM'!!!!!!!!!!3t!S9!lSÜ«!» •■■■■■■■■■■••■•■••■■«■•■•■■■■■•■■■■•■■■••••■■■•■■•••••■••■■•••••■BnBBfSSSfJSfSSESSSSSiSSSZSHl
4II1Jmil\u.J-LLL I) 1 i ; 11 iiil4-M4--U-U-4114- ll'lI'll! 4144-4444-4j4+ -444444 ittitrtti^#ti4±44^äSffi^m±a^ffiffiffi|ttffiS Ttrtfrrf- TTtt i+U Tj 111'. ffr t+t4- TP+ 2H1HE 2Ü ^^ 35 32 H5" 51S
■■■••■■•■•••■•■■■•■■•••*•••«••«•■■•••■••■••■■•• »■•■•(•■■•••■■■•■■«•••■■•■■•■■■••■■HHimni »■••■•■•••«•••••■■••••(■••••■•••■■■•■•■•••■■■i itmtiat ■■■■(•fiMtHiMitaiiiMlllTiftl (••■•■■■•■■■•■•••■■••••■■•••■■■•■■■•■■■•■■••••I
ZZliUZZZZZZZZZZZZtKSZZXZiSlZTZKUZKZZUZnZi «■•■•••■■•••••••■■■•■••■■•■■••■•HnMiimiiMit «•■•••••■••■•••••••■■•■■•••MMMinO!!M!!Sn!! ••••■••■•••••••••••••■•■•■■MhiWmMMifJM*! aaaB««BaBaBa»BBB«aaBaaaaaaa«aaaaaaäMaialaBa*2«««j
^^^4#^ ^# f#f ^H'H^ :^H:fe^ f^ ^^ ^^ ^^ Iff^ ^: ^^ ffrTt ^ iiaaMniHM*iiMa*M*raiaMiiiiM*iiMiMHi*MMM«iitHHMiM*aaaaaum(«a*a^ ia«MiiaaaiiaaiaiHaiiMaiMMiiH*iiaMi lltl**aal!!!!!!!!!!!USÜÜ:!!!S! tiiMiata«tN«iNfut*iMiMiiH*iM»MfMaiiM **lll"!t!a!'!!!E!!!!!!!>!:ü»!!ÜS!
naaaMiMaaaiaaaaai*aaa«iiiiii ^■■»■•■■■•■•■■■BBBaBBBBBBBaaiaia ■•■■■■••••■•■«••■■•■■■••■■••■•■
w?SSSä«SiiS5iiSSiSSSS?äa^wSS仫Tä«»»SK aBa«aaBBaaaaaaaa*aaaaaaea*a«an«*aa«»a>*aaaaa«aa«Ha^|2«*aaja* ■■■••■■■■•■•■•■■•■■■■••••••••■■■■■••••••••■•(•••■••'■•■•'•a1**1* SSiaiiSiSSSiSSSSiiSSiiiS •a"SEMafaaMSJ?MS£fi!22M522SSSIi «■■!•■■ ■■■■■»■■«■■•■•••••■••■••••••■•••••■•••■■••■••••••I
Jxttjtttt4m:tttt ;;||i;UJ:lij4.I^^4^£^fe^imM^B tSitui+ijagg !j]Tjii4i4ffi4ffig*4m HI jli iliffimffiMa
■aaMiiatmtia ■■•■■■■•aaa*aaa ■■■■■•■■•■■■■■■ •naiaaaiiaaaaa
••■■■■•■••••■■1 ::::::::::::::: ■■■■•■■•■■■■■••
aasä«aä*SSaaBB«BB*BaBaaaBB««Baaaa«*«aai#aasiaB*aa ■■■■•••■■■■■■■•«•aaaaaaaaaaaaaaBaaa»a«iiaiaaaa««a iSäSSaa«aaaaaaBaaaaaaaaaaaaaaaaBa«a««B«i«a«iaa«ai SiSiiSSaaBaaaa»«*«a«a«»B«a««flaaaB*B«*aai«aaaaaaBB
4141m m m mm mmmm^mmmmmifl MmlMIIIMtl aaaaaaaaaaaaaaa • •••■•••••••••••••■•■■•■••••••■••••••••M*«*IMf* •■••••»••■■•••■••■i iHiiiNtiaMBim
-j-i-..ij-t U-t- • »*J- iJ.-i i i t i) n IJ- 4 1.14, ,1 li.) 1144. t j i 1 Uli lU-i- 44- 4- 444- - 4 !>.[■ Hill +H aaäääaäiiäaäaaS ■■■■■BMBBBBBBBI
• ••■■•II ■■■■■■■■■■•■■■a
::::::::::::::: • •■■••■•■•■■■••••■■•■■•••• MMimik
aaaaaaaaaaaaaaa •■•■••■■•••■•■••■•■•M ••••■••■■■••••••••••••••■■■••I»
Miii|WMintMttMiii^iiiiiinit«»tttiii«iiiiiM»niinii|iiitnnimimiwitiiiii •■■■■■■•■•>■••■•• ■a«■■■■■■■■vaaai ••••■•■■■•■■■■1
•■•■•••■•••■■■I
::::::::::::::::::::::::::::::::::^:::BP::S::::::::::::::M^: ■••■••■••■•••••••••••■■■•■■■•■••»■■•»•••(••■■•■•••■••mvniaa ••••a«iaaaa«*Mt*a •»•■•■••■•»•••■■■E*****1!!*!!!!!!!!!*!!!
! 44-14 44-f-j- 4Q411! j 11 It 444T 4444 1 1 if ff44 4444 441- 444: 4444 +4+44- ffl •••••■■■•••■•il ::::::::::::::::::::::::::::::::::::":::::::::::::::::::::::::::::::::»::;;:: ■■■•■» ••■••■ ■■■■••■•«•••••••••■•■••••••••■•••••■■•■•■■•••••••■■•• •••■•••■••■■■•■■■•••••••••■••••■■•■••■•••■•■•••■••■••••■•■•(•■■■■■■■■•••••••ü! ■•■a■■••■a*•••••■■■■*■■■■■■•«*•■■■■■■•■*••■•«■■■ ::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::^^
•••■••••■••■■•••■■■•■••••M •••■•••■••■ !!/!S!!MMSSS!!!M!1M»SS»MS!*MHMSS*! «■■■««■>■■■■■■■■■■■•■■■■••«■■•■■«■•■••■■■«■■■■•■
nniM»Mitwt»ftniwittwm««tiinMMtiwiiMMntii>t»MMi':::;....MM«Mitn
•fiaafB?*?aaa»5""S?aafa5a*aPf ■•■■■!!■■■■■■ SSSSaaaa ■■■•■••«■••--=■•»Saa«""«""2""sr-M
■ ■■■■■■■■■•■ay'.itaiiitMiitiK*.:*«!***«^«!***.*«*!!*!!***!*'1***'*"**1*11"***1'"**1*****1111
••■■■••«•■ iMMm»iHMii»tm»»w»wwnminti«wt«MOTtMtiiiwn<initi'Kin»»wwi«WM
■ ■■■••••••• . ■•■••■•••••■■•»••■■■■■•■■»■■•«'••••••••■•■■■■•••|||*|*f*|"a*">l •■■•■■■■•• • ■■«•■>••• -■••■•••••••••■••••••••••••■•^«•••••••••••■••■•aiaij« ••••••••••
aaaa"äa»a^SSSSJ55arrääää"ääaaaaa"SäSSI"aa^
■iilliigtiwiiiiiinimMWMtwmtmiiiiiiMmtwuiMwiwiMttuiilMiiiiiii ■ ■■imM||Hllt»lljPtwmwlllll|H|ljttnttlWiWtlWIWWlHlltlllMWIHHIHlgl ff***tHtfHi«l ■«ttll(iltNMIH*t IliklMIIIIIIIII
•■•a a aaaa.- a »a •■■•■• aaaaaaaaa a i'Baaaaa»;;aBBaaaaajai;;fra);aiaaai a ••••••••■i ■■••■•■■■•■••■•••••■••••■■■•■•••■•■■■•■•■••■•■••••■"•■•■•■■•••••■••••*****i***a*l'a* •■••••■ •••••••••••■••• ■••• ■»■•,»M<,,,,ii,",:,'":!!!I!I!I!IIII!IIl!,!l!!!I!! :::::::::::::::::::::::::::::::::::::::::::::u::::::::::::::::.:::::::::::::::::::Mi:n::::::
• •••••••Miaa«**«fafifaaa«i«Maaaa«laBa«»a«ia««a«aa««aaa iaaaa>aaaaaaaaa*
M**llällUll'E!l'!'*'>,Ef**'U>!'l"l"*,*"""'i">*>(1 tf*«*ft«i*«Mi
::::::::::::»;' laBaaBBBBaiaBBi :::::::::::::::
•!■!!§!!■•••■•••■*••••■•••••••■•*■••(••••■••••■• IIIIIIIMIIiaiMI«H»l !■■■>■• iS«iaa*aaaaa«a*««a«aaa«a«a««aa*aBaa««aaaaa«aa*fBa ■5SaaaaaäSaaaBa««a*aa«*«B«««a«BBBa»«aB«if«aaaai«a •••••aaaa«■•■*••■■ •■■•••«-•■••••••«••••••••
,iimZZ»*m a ■■•■■••■••■■•■••■•■• ■■*■•• •••■# •••*••■•■• ■.«■■■•■■••■•■■■•■■••••■■■■■■»•■•»■•■•■••■•■••■■,»» !i■•■••■■■*••■••••••••••••••••••■••••••••••••■■•• •H •■•■••••■•••••••■«■•««••■••••■•«•NMII«
•MMNfMftnifBMitnminiinti iitiiiin fMit|iiNMtN*MttM«Mt(iMMMM»Htitf»iitni*«MfM«itti«iiimitiMtfi««i»T*ia
■»■■••■■■■■■■■ia ■•■•■■■••■■■■•a. ••■■■•■•■■•••■■I ■•■•••••••••••■•
■aaaaaaaaaaaaa«
■MiiiaflaiiMiiMiiatniii*Mia«mimnniMMn«ff«iiMMiiiaa*Maiiiii«fM«ii*nk'i ••■■•••••••••Ml
•■,'••••••!•■••••••••••••••••••••••••••••■•••••••• itti(Mi«««*iit«««« ••■•••«■«•••■«■■Miin«« ia«••■•••■■■■•■■•■•aa■■•••••■•••■•••■••••■••••••• ■•■(•••■■•••■•••■■■••■■••■■■•••■■•■••■•«••■■■•**a
»•••••HtaiMt ••■■•••■■■■■••■n«t wntniUffi ■••■•■ a »«aaaaai—aT—«■■■»■■■■■ ■■»»■•■•■••■»■■ a ■nimi
■■»«■■■■■■■■••■»■■■•■«■■■■■■■■■■■■••■•••••■■■•■•■I ■■•■•«■•■•■•••••••••••■•■•■••■••■••••aaaaMaaai
■•««•••••ttllll IIMMt«Mllff*(lt«l «MIIIMIMIMI •f««IM«tliMlttlllt«INIII«t»IIMIfMMIIIIIIHtlllttl(Mft«tlimill«tlllllMiltfM
aB*a«taaa«aaaaaaaaaaaaaaa■••a••*••■••••■•••••a • ■•••»•■••••■•••■••••■»•••■■•••■••('.•.••••f(
•■BBUBBBaBBBBBBBaBBBItB BB»BB«BBiaB«Bl iaaa a ■■■••»•••■•■■•i •••••■■•• ••••••■■■■ •aaras •■•■•! "^••^•^••«•■••■•••••••■•••••••••••••••••■■•■••I
• MMtnMINIMtdtMMinfilllMaiMflflltllflflfllttlllUDtMltattitMtllllllMtl ilHIIIM ■MilllM •■■■llllllll ■■aiftlillllii ■•■■■uiiaii
■■■•••■■■« i :::••■••• • ■•■■•■■■. •■■■•■»# »iMIIIkHIM ••■•■••■• ■aaiiiaiiii'i*aiiiiifii«a**it'iia*aiiii ai •■■•■•■■■••^■■■■•»■•••■■■•■■.'■•■■■■•■•■■■■■■■t ■•«•■■•■■■■•^•■■■■■■••■■••■■•^•■•■■■■•■■•■■■■i
iaaaataaaaaaaaa«aaaa«a»aaBaaa»aaaaaafa»ia«aaaa*aal ••••• ■••••■•■•••■■■••■■•••••••••••■•••• »••■•»•••■•■••••••••••■•••••■^•••■••••••••■••« (^■■•■•"■■•••■••■■■»•■■•a«aw»Ba«**«»»a»«aiaiBB»BBBal ■■■■•■•■■■■■■■■■■■•■■■■■•■«■■•■■■■■•■••■••••■■■■■I
Baa«iaaMBBBaaMvaaaaBm«saaaaaaaa8BaaBaBaaBBBBaaBBBBaBaBBBaaaaaBaa«aBaBaBa«BBaBaa«BaB iiiNtiiMiiimn
•»■•»••■•* BBBBBBaiBaB ••Mfviiiviiiii ■■•■■■■■in
• •■■•••■•••■•••^•■•■•■•••■■■••.' •■••■•*•■•■• ••>!••••••)••• •■■•••■■••■• ■ ■■•■■■■■■■•■a'■•■■••■■■aäaääa'äaäaaaW iaa5aaaB55i5iiSiB"5rSaiaiaiSaSaa5ii5iiSi5ii »■■■•■■■■■•■■■■■a^■■■■■a■■•■■•■■*. aa■••■•■••■•■■•■•••• ■••••■••■••••■•■•■■■•••••••••••■I*« • ••aa«aaaaaaaaaaaaaa"a«BaIä!aa*Saäa"aa^
■■■■•■■■■•iHrn ■■■■■■■■■■■■■■■■•■■■■■■■■■■■■■■■■■■■■■■■■■■■■■■■I »WliM»«iMill»M«IIWHMIHIIIHHIM«»m»M«»M«IIMMIWIM»Hl»l»millWIMHI M»WMipfMtlHl«HHtlWIIHH«»H»HM>HlMIHM WlllHllili»IIIIH»HHIII IIIIIIIMInmiMIIHIIHMIIHIMIIIIIiill lllltllMMIItllllUMIMiMIIII
■ ■■■■■■■■■■■■■(■■■■■■•■■■■■■■■■■■■■■■■■■■■■■IIMI
:";"";";::::::•■::.•■:::•■::•"- ••■••""•:*:::::::::::::::;:::::::::5;:s::;tjä]« ■ •■•■••■■■•■■Maääa^ ■ ■■■■■aaBaaaaaSäaa)BaSaia7«a'«aI«"äaa^ ■ ■aaaaaaaaaaaaaaaBaSaaa»ära.«aaa«a"iaB ■ ••■•••■••••■•BBaBa!aaaaBi"a"ai!a»'«aii ■■•■•■••■•■•••■■■■■•■•■••■■»^•aSSi«™»»^
«■»«■•■•■■■■■■•■lllii •■■■■■•■••■•■■•■■■•■■■■■■■■■■■■■■•■■«••■■■■■•■■■■■■■••■■■■■■•■■■•■■■•■»■•■■■■■■■■■■I
»»««•«••••••■••»•«•«••••••■■■■■■•••■••■■■••••■■■••■■••■■•■■•■■•■•••■•■■•■■•■■••■■•f
••■••••••■■••••
iiHiiiiiiimi
■::::^::::i;;::u::::::::::::::::::::::::::::::::R::~<»i>r.ii; •»•■•■•.'•••••.'■•■■••••■••I i ••■■■■ •••*• ■■■•■■••••■>"^»•a»i*»l
»■.*-..••.«••••' • *«**'**!*!!*>*a**M*^I*!!*^!l ■•■«•«Hi ■*■■■«■■ ■■■■■■■■■■■» •••»••••■■••■■••M ■•••• ••••■••■•■•■■■■■•MllltlltllMfM •■•■ tfll
naiMiit'iiiMii ■ •"•!••••■!•'■■ ••• ••■•■••■■■• äaäääaaiiaUl ••••*» • :::t:::::::::::::.::::::::u:::::::::tuin::n.': .•■•t.« I'MIII«( •••••••••••••••-«••■•••i Bit^BBBaiiBBaBaBBBiiaBaaaBaaaaaaaBBBaaBaiiiBi-aaaw^S *■•«•••• I*«I ••■•••••■1-fVMMtw« :•••••■•-•••<a. aaaa*! •••■Mf^£rrtt??SaS 'k'aaaBh'^BaaviBtiMa ■•■•■■■•■■■• •••••■■•■■••■•■•*•• ■ Ka>-aaaa?aaaa^ki •«.••'i* ••>r"«Ba.«a««."«aaaeaaaaaaaapaaaaaaaia«( •■•••••■• ■••N!M«k'>ai«.»MMMai«««iM«MMMii«ai*«t!ai iIii*3%"aB«.'iai>**a««««aaaaaaa«a«MaBBajrr«*a«H#« !•:•■■■'.«•■»"••••••«•• •■••••••■•»—•■•«■(• ■••••■•• ■>• ••■••••■•■»•i.lHaii«« • ••••■•••■.•.«•uMM«t ••■•■>•)•••«•■■«•
»«•••■»—•■■«■■•■«•»■■■«»«•■•»•■■•»■■■«»•■«■■■«••»■■■■■■»■•«■»••■■•■»••»••■miiMi* ■■■■■■««■■■■•■■1 ■■■■■■■•■■■■■■■■■■■■•■■■■■•■■■■■■■■■■■■■■■■■■■■i •*••••••■••••••■■••1■•••■••••■■•••■••■■■•i ■•■•aiiaiiiii IB *■•§■§§■ •■■■••■*■■ IMli«Miii»IIJ«»ll«M»MI«lf «■■
■MflMlllt««MIN«ll* ■•■IIIMllMIIIIIIIMI •••■•■»•■■••Mill ■ ••••■MMltNIMillra •••••••••(•■••■■tlllllll «■ MIMItlll BfifaiBMiaaMf a •••■•• ■■■■•■■•■IIMIIIIIMIIIIIIIIIIMI ■Kialawlilaali ■■aaiaiiimNiMiininiiiHHaiaiaiiii»
•■•■■rai*.llllll ■■BBBiiaJaBBBaaaa
ylpf ■■■■••■•••••aa■■ •■■■■■■■■■■■■■■a ■•■••aiaaa••■■■•
••■•■••■•••••■•••■••••••■••■■•••■••••aaa«**«*'**« BBBBBB ■ •^■•■■«■■IStlifSI**" •■••■•••••••■•••■■a*» ••■>>a
a ••••■•• ••• •••••••■■•»•••••»■■§••*** a aaaa**aaaaa«a■■•■•••••••■•■•••••••••aaa^a««*ff•• »■■■■■■■■■■•■••■■«•a •••■•■• ■•■•■•■■••«««rsaa?1.:* •••■•■•••■••■■••■•••••■•■••••••"•■••M« ■•••••■• ••• •••••••■•■«■•Maf««*M> ■■•••■•••■■•a« •••••••■■■•••••-^•••■•a* • ••■••• ••••••••••■•■■■■'ilaiNM*** ■■■■■■■■■■■■■■■■•••■■■■■■■■■•■■•Bl • •••■•••••••••••■••■•■••••MH«N»MI*Mimi«> •■•••■«••••••••••■•••••••••••■•■•••aaaUaaaaaaa* i*«iii! •■••••■••••••••••••■■••»■•■•••I
mm tfttIff:4tf 4n4l4t44Tilmpn tff if' 1 ■ ■■••■■•••••••■•••a aaa aiaa>T*
•••■••••••■•■•■•a ■•••■••••••■'waiil.« ••••••••■•••Hl« •■•■■••■•••■••(.••JMJJM* •••■ ■••••■••••••■••■• ■••*■■• ■■■■■■•■■•••■■I ••■■■• • ■ ••! ■••••• •••••••••••••••••■••MHIIMIIHIHMIXNMMM ■ ■••■•••••••■■••••••••■••■•• •••••••■•• ai •••••--.-•»•
tip rtjj-f 44ft 44I: ttmfat 44444 IilLli4ii- 4jt: | | | i 1 1 I 1 11! j 111 1 1111 |
4 44ft }4j 4ftf TtT tff TTnMi+rt 1 THI 1 1 " v\ 11M1111! ITTTjTl 111H11111111111111111111111111
aaaaaaaaaaaeaai
• ••••••••••• •»*«'■• ■•■•■ •n«a(iM*««*Mai«aa*iNaiiiiii«M** (•■■■■■■••■*•••• ■■•••• • ■■■■••••■•••a ••••••••••■•••••••••••••••va • ■■iinitH(i«tai(iiinaiii*fHiiniw«|iiii|Mi ■■■••■•••■••••••• •■•(••■■•••••••(••■•r<i •■•••• ••••••••• «fM** ■ •••••••■•••■■■•••■■••••«■•■«••«•■••«••»•■•••M ■•••»««»•••••■■»•»•«■•«••»a»»»»«»M>«»«i»MH.:» ■■■■■■■■■■■■■■■■■■■■■■■■■■■■■■■=?■ ■■■■■■■■■■•■•■■■■■■■■■■■■■■•■■■■■a ■••■••■•••••■ ••■■•••■■1 •■■•• •■■•••••«•■•■••••••••••"* •■■■■■■■■■■■«■•■•■■■■•■•■•■ aaiiiin im» ik'iamamiHiai«' a •••■•••■•••■•■•■•••••■••••■••■••••••••■■■•■■Ti ■ ■■••»•aa»ai aaMia»»»«»«»!««»!» ■■•■■•■■•••■■■■■••••■■■•■•••••■••■«•■•■••■■•■riB» • ••■■•••■•■■••••■•■••••■■•••••••••■•••■•■Ml» -■
Miillllill I
laaaaaaaaaaaaaa
«• •■•••••••■••■••••••••■•■«•■«•••»••I« ••■•■•••■••■••••■•I •••■ •••••• •■••••■•••■••••■•■••• «••*■• ■■•■■•■■■■«■■■■•■■■■■■•■•■■a••»■•••»•■•■•■■■■•■■• »mamiaaiiammiaaaaaaiaiaiHiuiiaHm» •■•■•■• ••••■••■••••••■•■••••■«■•••«•••I
•■••••••■•••••••»•»•■••■•■••»»••»■■••■••m ■••■■••• ••■■•••• <••••• •■•■•••■••••■••••■■•■••••••••••■•■■■••■•I ■•■••••••■•■•••••••■••■••••••■••M*Mti»ii»M«i • ••••••••■•••«•••■ ••••••^•••••••••■•■•■•M «•••«»■»•■«»•«■••«»•»■■••■•■•^•«••■•»■»»••••i ■ •••••■•■••••■••■••••■••■■■■•nan«»i»»iii«W
■■■■■■■•••«•■••■•■••■•■■••■I ••«»)•• ■«••■■■■■••■•■•imi ■•■•■«■■•■■■■■•■■••■■■••«■ • •■••••••••••••••»••••■••■•■••■••••»»»••■•M«
trttiiut Htflttt ffilafflSlllllllffiSt HIHIHI 11 1 iff H Mill III llllllll llllllll llllllll llllllllllllllllllllillllllllllllllllfTTHNll ill ill 1 11 +»4l444ci444V liui FflfffiJIlflMffll^^ mi im iiij a#4iBMl^^H^WIBlffiiil^BM^^^MiM Tm"!TiT trH' 11! 1 • Tr 1 , 1 ffr ffff iTTT 1111 11 1 1 1 1 1 111 Ml' Ttif i ilHil Iiilggjgl^Mtiitt#as l!lil!lllllljl|||ll|llllll!lll|l||||l|illlllllllllllllllllllM^ I iiliiii Hil HfitSSS4^444441 SISJ44444M IjtpT tftffijffifff^+mffifffi ' II 1 ||||||| |||l|l || ||
■■■•■■■■•■■•■•■■■•■■■■■•■■«■«•••■■•••■••■••••■•••••••••Ml ■■•■• ■•••! ■■■••■■■■■•■■■■■■••■■•■«■•■•■■■■••■■•••••■•■■■••■■•■■■••■•■■■•■I •■■•■■■■■■«■■■■■■••■■■••■■■•■■••■•■•■••••■•■■■••••••■•••••••••I ■»••••■■•»»»»•••«•««»•••••»••••••••••••■«»»•••»«•«•••«••■»»•«I« ••■ ■•■■■■•■•■•*• •••••••••■■•»■••••••••■•••■•••«■ ••••••••■••••■•••••••••••••••••■•••«■••••■••••••••Mjiaaiafi«a* aS!S*aaaSaaSSaaaaaaaaaaaaaa«aa»aaa**«a«««aCaaaSa*aa ■■•■■•■■•■■■^■■■■■■■■■•■■^■■■■•■■«■■■•••■a ■ ■BaaaaBaB«aBaBB*««««Ba»BBaBBaaaB*ai«BBa«BBBBatB«B«aaj*Ma««a*«a ■■• •■•«■■■■••••■•■■•••■■•■aBa»aBaBaaaiB**a«aBBlBBBff*B»a*aaaa>«BB ••••■•■■•■•••■■•■■•■■I ■■•■•■■
iit)l»iilMM!"»»*"«"«M"'t'"l"'"""«"»wi"""«nmmMim»imn»init • •■•■••aai
■' i j 1! j 1 * 1} . jijUl : j_t J . 1 j j 1 1111 111.. | |[| 1 ill . j: ±i.: 1 j j .1,111 J 1II1111111 H 11111111111111111 Uli 111111 fl 1 tt "tr "Tl"t T t*T ' "^ "^ •m- +t-*iT l!ll!!!!!!!!!!i!l!:;!l[H!!!!!!!!!!!!l!!!!!!!!l!!lü
MiimiiitiffiininiHtniiiiiiiiiiiiiiiiiiiiiiinniiii (»«»■WinmtumiminniwttmwmiMmiimim» IM|MIMllHplllltllMIIIIWWIWiHMtWlllMmilllllII •MfitMiM«iii*Miin«tiiiiiiin ■ittiitutMitiiti ■«•••*•&! «■■»■•■■■»•■■■■■■■■I •»#■•»■■«•»»»*■»•■■■ ■■«iiMiiili»n«i»ttwnittiimiM«iww»i»n«iMnmii»ti ■ ■»■■■■ttmitlMIH«Mt>WIIW>«>M>IWWWiW»IH>tl MlliitHniiiimnitiliniliniinnnmilnliiimmi P*•*■•••»•■«»••■»•••■■••«•«■«•«•■•««■■•■»•■■••■■■■•■■■■«•i ■ ••••«««•••••••««•••••■•■»••••■««•■■■•■■«•«■••■•■•■•••a
n«i»«>mi immun
«■••■■••••••••«•••••••
«»•■■»■■■«■»■•«••■■«■■«»ei •••••••■••■•••*«■«••«»•••••* • •■•»••••••••«■■••■•••••«•a
• i
«■»■■«■■»■■■■••a«
• t
11 n M t n I n 1111 ii n 1111M111111IIH11111111HIT1111111111 n in I ii 111111111111
-tj±Ltol± Tl4±i±iiitpt±tj±±r-uiJii35^yir[-)-|rtrfrtTf 'iji ll qromBgifi 1 i 1! 11 f M H t ?Tf'H:fWTf]ff-fH:lT' t i t i 1H111) M1) 1 i 1 ITT m-JiTHfUjIillUIIUUI ;±t]iLtttt
HT3^3|S^S^^^^^^^^^^^^^^|^ mffllSffljjiltHl |i|| g^^gs^^^s^ära^P^BBp .1 LI |:[L -j. itUll. xtt "tti-t-
^l^g^Sg^äl^^äs^^^g^^^^g^^ 1 | I '; 1 1 ■
^B^S^SSSS:^St^fPP^Wpl| 'fHHttp
i4-ji]-j-»H~ Itf^TtfrtUl!f 14*!'+^~^^illli-rlj-r iilJlliJI-1nrTyiirTTH 1 [-TTf THTTJT -trj-fl-fjtr t+rr ^ttr" rj^ jnt fftt -fttf TtT' Ttft M' 1 nt TTM "fttt 111111 FTT TTTT f TT
Sf+ttrrt 1 j jl i tttt f TO
4-;4Jt-*-tJ4- liu U1*. t-ii" t xttr X nt? "ttTl- TTT - ritt" TTTT 1 ill 1111 rl ii t'li 111H" Ti 1 t~ TTI 1 mm
iiSfiiiPliiSw:ffiff ftlxSa .j-i-l\}\\\] *|'{t{f"|jf ffff "ff^"ffif "ffff •jffl'?ffi irljj'ffii tfrj"^TfJtTTfltttt ffiffrfofff 4-tiJ- 4ftt -*"*■ ■♦■ -^*t ■ ' 111 [ ft"* 4- ++- ill' 1111 rfc 41 *TT|*p ! j j | - {j i {' 11 M t"f 111 j 1 "ffTJTTT TT
ttttl-rH Tkr-^^ttttttffT^STTTTTII^TrTi ~^f^7^^~?f rr^rilH4tiT^illti-S s üill^:S^M^ffl:ffilI^ffi:ffl^^^^^l
:±^ittiJ± TJtjfJTtT Tr^rf M ■r
^^^^ ^^^^ "^;al-^jj|jjj{jj xZt^j^ "fe ^^ ± ^ E ^^^^ ^ ^^ ^^^^ ^^^^ E ^i^£ -fff Mffiflilftfl ^^^^£ ^£ ^i'5
HBIIIIIIIIHI^^H Ir 111'Tnili TtTiTrH"'"1
R+tti-iä
i^t^tH.jfff HtnlrrtPllT^^f :fffft-ff*ffTm:llllllllllll[[llllllllllllllF ttftj^- ;mg:HBttttjBBffBgBg^ i^jsi ^ Tit liit
x?r -M-P- ^rffftf TfTffff ttt vff^: tp- itff t tt T tt tttt'"' 111111 ,rti 111111111' 11111111 n 1111111111111111111 n 1111111111111111 n 1111111111111111111 rri 111111" tit t t^t E^^:igft1f tiff fit :ff:::ft:1ffl:f ff f ffffff Mllllllllllllllllllllllllllll1 BH *-».*-♦- T3X" ■ulr J-i j II 111 ' lr 4X"'. rtr 1 .J.J I.I.. I xr x irt Ml ! 1 1 11 111 111 1 1111 rn* -V+- M-GXt - . -LX . XL .J 1 LIIJ.C 4-LL - -| - XT . 1 [ j 1 X IT I TX Mil . .J_Li_i.iJ.j.l III II I I 1 lit [ | | 1 1 rl
fflt+gq rff .tt i ttr itt- Itt -Jtr tlMlTlill!': ^ ± Itt: trrr ± *: ±: ± oft 111! 1! 1111! 11111111111WJ-UU-
is- #pfffc:ifi^fP:PiPjllillllllllll^^B ^:^::^±ggig:#::H::::Etft:}:f^^:M yifflrWrfflt SK5SR
■t«.4 *l 111 J -j-1— 111 j 11 XL - -Lj-yi vw-f-f- —r+ ■[■I'M" r - T 4T TTTT 111 ill 1111111 111 ill 11111 i 11 -f-f f ■ jT^-H-!
^P^l ^I^KBBIIWP-PIIBIIIIIIIIHHlf^^B BtErtH
fStjtki I j-itf jjw EEBBE±S5S|^^^ffl ftfffrillTiS IBB
jHHJIJl^^^jjp: f'*'t i ttrrr j-' } { ' j,?7T'
i TrTttt
gigggllljpB tbrirpr ttttfrttf ftffffiffiff^fffi tHIffltT TTTtflftrTr ffffl
ttt^iHi; trfr—^-*-f-: 1^ 1111) 111 :l j' i j | -fiji-H-P-f« ijtirtt&j
Tterffi ö5ESij3
Ettrjtj ifll "Bit tji:i1H'-BllSH|mSffiroffiHB:^^^ffl^ tjtft It ffffl t fHT^f-H^ ttitTTrtj
•tiii mi iH:|:söS;H|;-:ft^#Si++llÄ4+l4mSilll^^^TO 11 | ' T "H" j i '~tr W#j ^SltHl^j|:p||jj§§|PgpP§l§iJj||||[|||||i mtitUii liüiffii M^lllillBiiBBsiitWilTTWi EH3^nuirn*iä;ffijs±Hl!li rifl,:;:: ::iJm:3 ttgjffiMlBglBgffff ffiff|||||ll|| fgg|l||l|||||||j 1-Eii SH EjlE^jt 3|! tg ggt 331+2 ffi ^ gg TTH'JW' SSff mWffifffffi
llllllll TTTT i tm"Ttth li-4-i-i.j..4-i-t
OT^x-it ■ TiT*iTr~*~f
4*i44-i+ti
St2Ä£ tjlj-H-rji jp\ -H-H- +Hf :H-H- tt + -1414 JW Sfi 4+jl +ff jt 4*t II UrkK/UJil "Hit Ttlirtit H j 1111 ui-r - ffpfffi+S :SEiir}-i-jj--|-j4i44l-*--LM- ^^ ^ ^^M^ :^R::fc "H~H" *HT ^^ff ^^^ ^^^ ^^ff ^^ - ^¥ ^^F ^^ ^^H-J-44-M44-i-
mfimntTm il i'P " Tn ) {1 M H T TT H"H HT-
• V'
lt^jT..,l,,.:l,,^^l^j3^y^llt^-^^+^^ JUIjftTj- HL
i^H ttlBfS
te^i^^lipH ■miniminrnittt niiniimiiiiiHMiiiiiimiiwt iiimiiiiiinmiinumniiiminiMWiinwiiinniitnii IWUMHWIIWIIIIHI IIMtllllMtlll» llllMt —aääaaa aaaaa aaaa■ aaaa» WWM> ■ftaaamaa laaamawaaaBM •■••■■ luiinn
•am aMari MaMaBna§MMaanMaMMa*MMiM«MMMMMaMMMM •■•••■•••••••■•
BBBBBBBN Maaaaaaa ■■■nana •••■••••■ •■•••Maa ■aaiBiaa«
aaMtiiiM ■■••iiavaa ■■■aaiBBBB
■ a«*«aM*a \v.r.\::z\ ■aaBBiaBai aaaiaaBaaa ̂
iM^?f itrÄp;
BitFilT rffifrt "f TftT "^"^ "fl"^" frT "fttt "M" i trH""H"!
MinraiiiMtiiiiiKmiNMnanMiiitiiMitMiMMiiMtiitffiiMitiffiiiitii mitflMMIttraii nlMNItlMMItlM«lllll«lftllll*lllttlll«tll Itl IMMMMIIUMWMMIMMMWtlUltlttMMUtMtlMUtMMWlMtlHWlUllll inniMMNIMMIllllllllMIMMIIM II1IIMIIMI Itlll niimiHMiiiiiiHii
•aaaBBarata
•■■■■■■•a •• :::::: ::j|:::::-HnnH:: iaaaaaiaaaiaaaaiaaaiaaaaaaia • ••aaapaaaaaaaaataanaaai an ia«Hiitaaaaiia«aiaa«aaaa i ■ •••••■1 B1 l^;
■iitranMiiiiiaiiMMiiiiitMiiiiiMiiiMiHiiiiiitttiiiiiiiiiiiiiitMMiiiii ■MtniiiiiiiMiiiiiM • ■•■••• MMMMMMMI
MtfltMItMIIMMMMiniMlltMtnMIMIIMIMlIllltlllllllltlllMItMIIIIII
■ ••■•MM •••••MM •■•••••■■ ■ •••■•Ml
•MaaaMiMMMMMMiMa a
■ aaaaaBaaaaiMBMaaaaiiaaa M •■••■■aaaBaaaaaalaaaaaMMi a
ilil Ij-U- .ij.U-Ti4- -*_*.*_"-i-ix j-1i 1L11 li J,llLi 1.1 j 1 x lltl till ** J-.I-.-4T .Tltt i 4± liif iftt i ■ijJj.tj.I4 ü -H *
■ ■«■■■■ffMMtMllllllfltllllMItllllltMlltMfttlllllffllllllllMMIIIMIIMi
iMtiiMiftii»ii »■•■»■a«aaa»»«;2.?a-r:ia»»aaaaaaBiBBapaa*-- iHiiiiiMiiii::.«;;»'
••■^•■■••■M«IMIItMM*MnillllllM';«'.a**.«ftMIIIMf«i>-^»ri>%f; mn ■■■••»•••••••••[••••••^»^■f.iimii«MiM«^di^*'Sif*'.ii
••■••MM ■••■■•••■ ■MMMH
-::;:;;iss •■&■■■■■■
•■■■■■■■•■■■■■■iaBaaaaaii a ■ ■■•aaiB#aaBBBBiBaBB8Bt>a« i ■aiaaiiMMiiiaaaMnaaaBl a =-—j-faBB^i-aBiaaBaaMaai ■ ■ ■■■■•i*«i«r#*9r*.f».•••■■* a iaBaBBBaia«i«BB«a»*'«aB8BB 1 ■••lafaaaMiNiiiaaiinM a ■ aaaa*>«***älF<ita3aaa*aaaaai •
iiiiüHiiii 1 ft 1t1tN"trrtt1ttlt'ttt"ttl"-' t^ffffTiffTffflnf fflMWro |9»:i|f* !:s:::!:: IP ■Iiilfflii|iii! TT trr ■ trr ffff ¥' ar * "f T ? ?Ps w wf TOT TTTT Tmrrrmw ■aalit'll
•tun-ail ia»aaifiaafBtaaa|alB«BBaBäa laaaC'iaaataaaaaiaaiaiaaaia
imnii itffflitiiiH*itaa«?a«r'<*tiii IMIMII iMiiii»»*** •■• »•»■■■■■■'■•■■■.*■■»**»■ ■■■■■■Nimir<0'j'.ftlill*»jUt«;ui ••■'.■■■■ ■■«■■»■■
■■!■■•«■]■■»■■■■■ •gMSF^iaa ■§■■■••■■*■ ••aBBcaaaaaaaaaBiaaMiiiaiBBaBaiaBBaBaaai aaar<aaa:aaaa*a*aaMaaaaaaiaiaaataa*«i ■»«••••■••■■•••aMM*MMaaM«aaaaaai
aaaaaaa» ••aaaaaa
•■•aaaaa
jjfflr^ :^^^^ ^mj^ ^£ ^S ^g ^g ^S i: ■■■■«■'. mv^'j» ■■■■•■«•« 1 -■aflawara «*■■«■■«■«:■■■■«■■■■« um* ■ ■ ■ ■»•^•«■'jaa ■■■•■'<■■■ wi ay <w;>T^i»a—■—r>s lp» ■ a ■■■mtiiit^i ■■■*.pw»5 inrjWil'iHIIM !■■■*■■•■■■■■■■ jaMfMnfas^a«»
r^aa-j«n«r-«BaaaBsar>«Si mr.irnif'niiiH'SMiiHm •• r iirnntMiiinr
■•■--i—mm inia>aaaaaaaaaaaaa»aaaaaaaa» M«aHia aa a atf^a a a a ■■—aura iiti iMMaaaaraaaaaaaaMiaaaaMi
■■•••■•a
sar:sl
"|.| M 11 > !-■ TIT?- -H-M- -i-M-*- -ft A n-T^ +ff ■ TT-T Ü+ +H1 ^ ■■•■•••aa aaaaaaaaa
•aaaaaaiMaMaaaaaaaaMM« ■•■■■■■■■•MMaaaaaaaaaaaai
■•••aaaa ■»aaaaaa
i^jj-Ulf -tul 111 1U14-j-ü' ^li+ -ffij- -j-j-ij ■ -UJ-j. -jiiffi-i-j .Mr «MM M will MI a ■•ssawsiia teaaM MaMN*M>oiMiiiiii UHiiiNin'iipnaa«'*M*mMl «■■■miiiiNiNmimiiiii ■■■■«ia*!:Sa««a ■■»■■■■■»■■■■■■■■■■■■■■■•■■aaaa««a
■ aaaiägi 1 ■■ ■■■■B ■■ aimii ■!■■■■■■ ■■■■■■ni
aanaiaaa ■■•■•aaaa aaaf ■•■••■
IB "»•»•»■■• •••■■! ■■■■■•■aaaiaaa|iai ■aaaa8a***BBa#iaaa
:||j | ^j
^^iffi^ffi^Mffl;gi^sa ■«■■■■■**■=*•**»■■■■■■■ «*»-i«aai laaaaaaaaaaai ■■■■■■■■in glfal»!»—■■■■■■■«■—■■■■■■■«—■■■■■■■■!
HtHHI IIINIIIIMtillllllllllllilllll ItllMIIIINMIliillllillllllllMII liinii Mt ■••■• »in •••*»■••••
aaMMMBi aaaaaaaaa
aaaaaiaaa
•aaaaaava ■aaaalBBB ■■■■■■an
i aaaaaaaaaaaaaaaai
■ aaaaia aaa a a a«««*aii
aaaaaaaaaia ••■•■ Wti
,ii|i iii Tit T£ - - Trt"! itt i iti -it" it i - it. tin Ü ■■••■■■■■■■■■■■■■■•■■■»■■■■■•■■•■i ■inillifiiiiiiiillili »■«■•■•■■■■■■»■■■•■■•■■■■■■■iiiti aaaBaaawMaaaasaaaMBaBaaMaaaiaBBaaaaBaaBaaaaaBBBaaBaBaaaaaBaaaaaaaaaaaaaaaa llltlMMIItMl »■••■•■■••■■•■•fl Itllllllttilll ■ IMIIIIMIIIMIimillHtlMtlMIKf «■• miniiNMiNii ■Kinimmn ■■■■■»■■■■■■■■■■■■■■•■tim ■BW*BBBBBB»B««a
aaaaaaaaa ■••■••■■■ •aaaiaaaa aaaaaiaaa' aaaaiaa«a
•■■■■■■■■•■ aaaaa ■■■■•■•••••••••■« l^ra
iff^f'fiflr^JMflSffii^ll^ff ■■■■■■■■■■«•■■■■•■■■•■■■■■1 ■■■tfllllltlllllll« «■■■anniMi ■•*■*■■■■■■*■■■■■■■•«■■•■ ■■■■■■■■■■■■■■■■■■■I »■■«■■•■■■■■■■■■■»■■■II •■•■••••••MI (■■••••■■■•■••••■■■■■■•••■••■■■iiiiMitiiiiia ■■•■■■■■■■■■•«•■••••■•••■■■■•■■■••■•■•■■■•■••«•■•■•■•■•••■•■■■•■•■••«••(•■■■•■••■•■■■■I • ••••••■••••I IM • • •
aaiflaaaaaiaaa laaaaa Ma ■•■■■
aaaa a aaaaa Kam Sni
::R::UI zr.iirA ■■■•••••I •aiaaaval
laaaa••■■»« aaBBMaaaaaaa» itHMMitmttt ■w—gg;-M ■■■■■■■■ ■ ••MaaaaMMaMaMaaaj • ■••■,<:-• ■ ••••••aBaafcaaaaaMMaaaaaaaMaBMaaaMM •*■■•■•••■••••■•» ■ aMmBaaaaaaaaMaaaaiBaaa aaaaa aaaaaaaaaaaaaaaBaaaaaaaaaaai ■ •*aaa>aaa«8a*>aBaa«jaaaMM«B*M*Maaaa*aMM#aa ■nittmirai
■■■■■■■■»■«■■■■•■■■«■■■■■■■■Ml ■■•■■! •■•■■•«■■■■•••■■■■■■■■■■MMIMI ■■■•■^«^^•■■■«■•■■■■■■■■■■■■■■■■■■•■■■■■»■■■■■■■■■■■■■•■■■■■■■■■■■■■■■■■■■■■■■■■■■■■■l ■■■■■■■«■■«■■■■■■■•■■■■■■«(■•■■■■■•■■■■■»—;«:;—::::=9:?-r—"»»>»"""""«™»»"««»i««
•aaaBasaai ■aaaaaaaaa« aaaaw !S!!S!S2f£S Hi!! sSs
TP^""T' f frv 1 ittT"fntffT HP"HTtntiitrfr ■■■■■■■■■»■■■■■■■■■■■■■■i aBBBBaaiBaBaBBBi ■■■■■«■■■»■■■»■■»■»B ■■■■■■■■■■■■■■■«•■l *•••••■■••■•• ■•■■■••• MMI •■•• ••••■■■■••I
•■■■■■■■■■■«■■••■■■
• ••••MM • •■•»••aaaa
lop #5 BEEEE Stt BEE if 1 i H Ü1 ajitiifflB.-^mi^-iirtett B±:BEBEEB
t|itiatm^gti||ii'^ff|fff 1 JIM TUTTF
■■■■■■■■•!■■ ■■■■■■■■■■■■■■■1 ••••■•••.1*llMI«il'|l|IIM:3»a>l«»lM«lMK<MI'*'11M.<l>U(MMMM ••••■ MI ■■•■■■■■■■■•■■■■■■■■■■■■•■»•■■■■•■•■■•■■•■■■■■i ■■■■■■■■■■■a MmiHinifiaiim ■■■■■■■aaaaaai kMiMiMii ■ ■■■■■■MMIII :■■■■■■«■■■»■
■■■■■■•■••■■■■••■■■•••■■■■■■■•■•■■■■■■■•■•■•■•••■■■•■•••••■■■••■•••■■■•■■■■■••••••••■II • ••••• ■••• ••• MM ■•(•••■ ••••■• »M1I1MII • •••■••••■••■••■MMIIIMMIIIIMNIIMMIHIIHNMM •■••••••••■••••••■•IMIMI ■ ■■••••■•■••■•■•■■•■■■•■•••■■•■■••■■■■•■■••■•••■■••■•■••■•■■•■••••■•••••••■•••••MMMI ■■■■■■IM ■■*■■«■■■■■ ■■«••■■■■■■■ ■■■■■■■■■•■•»■■■■■■a •■■{■■■■■■■«^■■■■■■■■■■■■■■■■•■■■■■■••■■■■■■■■••■■■■■■■rBBawaaaaaaaBai
»•■■■■ BBiiaai ■••■■••••■■■
•■•••■■■•
aaaaaaaaai
■■••>••> a a an
|l["||i|;JUtj:r
■ | {{ 11 j - T -j-|l' - 4- j} ] f | [ j- -t-j-Tf- - -T
s^
Bff^Bfip5:S^Si::i:^ffiffiS ijB Bii. Eh ±g:: BE t B BE: t B BEE 1 Bp BEE E
piii|8li«il
aaaaaaa»«aBaaaaa«a3aaaaaaaa«a>aaBaaaaaa■■■•■•••••■•■•■•■■•■•■■■•••••••■■••■■■••ääaMäää ■■■■■■■■»■■■•■■■■■■■■■■■■••■•■■■■■•■••■MMMMMMMMMMIMMMIMIMI wiiiniminiiii» ■■■■■■■ raiiaaaiMiiiMM ■■■■•■■■■■Mn»aiMIBIIMMHniMaiail*l>aai>MMMIMI*MII*M«IM(MMIMM«M«liaM ■■■■■■■■■■■■■■■■■■■■■■BMMBaaaMMMMMa ■aiMiiaiiMHHaaaaiaaaaii
■■■■■■■■■■■■■■■■■■•■■■■■■■•■■■■1 ajaaBBBaa ■•■■■■■■■■aaai
a»»"—"5=S—■■■■■■■■■■■■■■■■■MMM»^:. ••••■alM««iMMaaaaMlaaaa««if*<a*^*'ia i*iaaaaaaia«M>iaa«*ia«aia ••■aaniiinatiiMiiiaiiMt-.Mr.a^aaaaaaaai',«aw'.a«.aami<aiHaiMiit«t*iiaaiaaiaa»a* ■aaaanElamaaaaaaaaaiHa'iaiPM^»aHHaa,:aaaif«a<;<iaaiH*iaiiMaiiaiaaaaar.taaf«B:;äaMa BBBB>aBlBaaaaBaaaaBBaia^«av,:a^aaBaaBBBKCaiaaar&BsiaBBBBBa«BaBaBBBaaBBaBaaa**=^aaBaaaBBaBB aaiMaaaa«aiaaaaaaaaaa.*l'<r< a'jaaa'<a'.at>aaaaaaaaiaaaataaaaa*:>a>>'r::-aataaaaa n«MMiin«aiiaaaarai»aF'tMaaMa',aa»*4i*<aaaatBaaiMMaMi>^.a;^g««"T:<MiMMaaMaai
aaaaaaaaai
aaaaaaaaaa ■■••••atia
BBaaaa'jü.ia iaaa*iMai
aaaaaiMMMaaaaa aaaaaaaaaaaaaaaa* aaaaaaaaaaaaaaaaa maiaaaaaaifaaaa aaaiaMiKNMin
::»::::t:r;R:h ** artip • aa»a Maaaaa ••••■•••■•••aiMa
(aUaitiMMfMH- (•«»auaasaaaaaua
B||;
|^^;|||lil^pSll:Sffil itaa*a*aaaaaaaaiaaa«faraaaaaaaa-,ar,«ii'.a aaaaata'.ua^««'
■■■■■MM
»•nuati aaaa'aaaaaa MMaaaaai
n:::::::KgiJS
•Hr-THT■ rtt nf-frr +ttrrt+Fxitttrfr• rFrBEBF T " Ttf" TT TMT?1 ITT' j'-Hjr TtTT f 1' ntTTTnTf 1 m'Hl'TrHTfnTfHiTrm I rrT 4Bffaat-zwi =<aaaaaia* irt j—H j 1 j i ggj
:F:iiHi: tfi^IBPEäög±^:a^:SgÖe ■ljuJ ■ ■ r^iti|B|F^ffiil^ilrlffltntfflTHl^^ff^ ill!
lipi mt-f'fF^ iBBBttiti Bi|i:::±tti;
^
ijii fei MmMMWMiwiWä r-q-Sti 1lErimmäjgai§iBtB^^S ii;-! t:{i tiit fig BB |EEE BEE r B BtBEEtl tj# it
SMl^K WM iB Si * 1II1
iariaaaiaaaKaaiaaf*-..»*^iiaM:*aiiai**-.aak.'iMM(ttMMMMMiMMMiMiMMMiMMa aaraaaaaaa laxaaai ■T/BBaraa ^—^■«■■■■aaa ••■■■■■■■■■■■■■■ •»■■•«•■•a ■ ■■■m5i>aman»—i«t*-=«aJ)»»-i*i«»riaai«»lBi »i^aaMi iBaBaaaaaaaaB aiaaPs«a''Sat*'SS«aaa*>=rfailaaa laiaiaaiMiiMMiaM ■«•&'?£■';•«• ■■■■■■■■■■■■■■■■ ■CHiilH»':;«MM»iM«aMiaMMaaMa«aaaaaaa«aatMi«aaaaaaaaaaaaaaaaa»Ma»aa«aaa»MaMa
•■•■■■■■■—ai «■—•■■■■•■»»■■•■■■•■■■■—»■■«■««■•■■aa
■ ■■■MB ■•■• ■■■•■■■■•niiiiiiaiiiaaiaiaaiaMaRaaaiaiaaiaaaianaaiHaaHaMaaaaaaaaaaaaaaaaaaiaaaaM
■■■■••■■■■••••••■•■■•«■■•■■■■■■■■■••••••■■•••••■■■■•••■■•••■■•••••••■■■MMMMH«I«IM
•aaaaaaaai
■ aaaiiMia
•aaaaaaaaa aaaaaiaaai ■•■•••■■a« •■•••■•■•a ■•aaaiaaia •••■••aaaa ■a Baa aaaaa laaaiaMai
HI 11 jHB
jjj [1' IT! h
fntfti
$ifö!t Ögjgö iitisiiiiitllilli
iiiiiiiiHiiiuiiiaaiiiamiaiNiNaaiiaii iiiiiiiiiiiNiiiiiiiiiiiiiiiiNNiN ■■■•••••■•■■•••■••••■••■•■■■••••••••■■••■■•••••■■■■■•■■•■■•••••Maaa«Baa*aaa(*iMiM«M
MaaaMMMMMaaiMa*aaaMiaaaiMaMMBHM«aaaHaaMiaiMMai«*MMiaaaMMMaHMaaa »■■■■■aasaaa«
■■■■■a«aaaaaaBaaaaBBaaBBBaaB«aaaaa«aBBBaaaaaBBaaiBBBBBBBBBBaaM«BaBBaBBBB*B«aBBaaaaaa«Baa ■aaaaaaaaai
•daaaai* ■•••••■■•••■■■•■•■«•■■•■• ■••■■«•••••■•■■■■••••■ •■••■•■■■•••« iaaiaaaaaaaaaaaMaaan«a*aii»aa«a !«■■•■■■■■■■■■ MMMMMBaaMMia a •■••MMHMa«MiaiMMi*iMM*(liaaa«aaaaiaaa*aa«aaiaaaaaa*«aiaaaaaaaaaaaaaa
■■••*•*•■« ■•aatiaaaa
•aaaaaaaaa •aaaaaaaaa aaaaaaaaa« ■aaaaaaiH ■■•■•aaaaa
■Baaia aaaaa aaaaaaaaa«
::: ■a a ■a a ■ai ■■■ ■a a a: aaa ■■■ •■■ SE f-f (-j I'^'I'r*-
iiBit
lilt j-rti tu; ttatti44ti±tti^isä:ffiMS hu ■;:■■ i:titt;t!-ii}::iBFtttii|#iffi:5?agä TiT!~ "irt 7^; TJT *rrriffrTutffir tfff nff Ttttff
■••■•■■■a
■•■■«i«äiai.*>><<ijSai>6wl«Wiia«a*>«t«>««Bk^Mcarai*aB>.-5ia**>--
••■MMMa
■aaaaaaaai •■•
■a a •a«
■a iaaa iaawiaaaaw ■aa« aaaaaaaaa■
aaaaaaaawaaan ::::RKKB»
If 3:11
tUi.iij-i Li:^"ylliXI- -l?^ -*^HT -*lfr"Mir ITTI" L iff TTTT "H" itlt ttlti*-«-! 'T^Tr 1 iir !! Ii it-H- 1 i! 1 j 1 j | "-H-J- 1 i H ir
.*; j j "ut* -L|-i-iiitji-!' 1) l'ji i j i i -j-i-H-1 j! I j j j 1 1 j j j +f
•«aa»M«MaaaM»a»»MaMMaaaaaaaaaa»aaaaaaaaaaaa«aaaaaaaa* aa aaaaaaaaai iitamtNaa«aaaaaaM«"itaaraautaaaaaaaaaaaaaaaaaaaa«aaa«aaaaaaaaaaa aaaaaaaaaaa« aa>««Naaa<aaaaa>wtiaB«a*BPaaaB'ir.a<.-a*,aa*iar«aaaaaaai**fa">aai* •(<■■■■■■■■■■■■•■■■■■■■■■■■«■■■>■■■■
•■••MLi^«MiMMaaaMMaaMiMMM«(i«*«MaaaM«M*MaaaaaaaaaaaaMa(atiaa«aat«a«aaaiai
■••■•••••a
••■••••••a »•••••••■ »«aaaaiaaH laaaaiiaaaaamaaa
•••■•••••aaaaaaaai •aaaa•aaaaaaaaaaa
S§^ ^
■■MMM*aaaMaaaaMaaaHaaaaMaaBM*i*MaMaat»aMiaaM«iMaaiaaaaMa«iaaaiisH*aaaMi aaaaaaaaaaaaaaaaa
■••a«■■■•■•••aaaa •*>•<•■■• aaaMfiaaa
xnitt:* •tM«MtMltff«*MHNW*NMfMfMMINflff«t«MIMIIMI( iiaaiiiaaaaaaa ai•••••*( «Maaaaaiaaaa aaaaiaaaaaaaaaaiaaaaaaaiaaaaaaaaaaiiiaaa ^fft • ■■M««tMllfMttl*ll*i«tI*fflMf«ffll«ltll>IMt*«tfl>tl»r MiiitftiiiifninMniii>imiMi*t»i*iiittiiiitniii*it
lattiiiMa ■•■■•■•■■••iiimiiia IMIIM • iiHiiiiiiiiiiiaiiiMHaMiiiiiiMMtNiaiaai aaaaaaaai maaraaaaB !•■»■■•■ ■»'•It)]
%m
rrrrm:
: j-u..,.!..., . r,. r.
■ftrttttra'-.tni
rnzrrq
■Tn#rHf$ti ■