!J:A '!:tJS':'!TUTE OF TECHt!OLOGY UTE OF TECHNOLOGY !f...
Transcript of !J:A '!:tJS':'!TUTE OF TECHt!OLOGY UTE OF TECHNOLOGY !f...
L!FCJ:\!J:A '!:tJS':'!TUTE OF TECHt!OLOGY GGENHElM AER0NAUT!CAL LABORATORY
JRANDUM No. 29 UTE OF TECHNOLOGY
!f - AUTICAL LABORATORY ------~~----~~--~--~~~
HYPERSONIC WIND TUNNEL
Pasadena, California
MEMORANDUM NO. 29
·'
July 31, 1955
INSTRUMENTATION
OF
GALCIT HYPERSO_NIC WIND TUNNELS
by
Paul E. Baloga
Henry T. · Nagamatsu
IN U
..
. .
•
SPONSORED BY ARMY ORDNANCE AND AIR FORCE
CONTRACT NO. DA-04-495-0rd-19 .
Contract No. DA4-495-ord-19
A.rfn7 Ordnance Department
SponsoMd b,y A:nq Ordnance and Air Force
MEMORANOOH NO. 29
INSTRUMENTATION OF GALCIT HIPER:iONIC Wnm TUNNELS
. Paul E. Baloga
Henry To Nagamatsu
~w-4<&-Guggenheim Aeronautical Laboratoq
GOOGENHEJM AERONAUTICAL LABORATORC Cal.ii'omia Ina t.i t.u t.e of Technology
Pasadena, California
~ .:n, 195S
TABLE OF CONTENTS
PART PAGE
I. Introduction 1
II. Hypersonic Wind Tunnel ~scription 2
A. Leg No. 1, Mach Number Range 2-7 2
Be Leg No. 2, Mach Number Range 4-11 .3
III. Compressor Plant Instrumentation .3
Ao Variable Concii tions Indica ted on the Control Panel .3
le Inlet and Outlet Pressures for Each Stage of Compression .3
2. Outlet Air Temperature for Each Stage .3
.3. Compression Ratio o£ Certain Compressor Stages 3
4. Stagnation Pressure 4
5. Stagnation Temperature 4
B. Description of Measuring and Controlling Ins trurnents and Techniques 4
1. Operation of Tate-Emery Pressure Indicator 4
2. Method of Stagnation Pressure Control 5
3. Air Temperature Control 6
a. Control for Leg No. 1 Steam Heat Exchanger 6
bo Control for Leg No. 2 Heaters 1
IV • Pressure Measuring Methods
A. Low Pressure Silicone Manometer Banks
B. Low Pressure :t-iicromanometer Bank
c. Tilting "U" Tube Micromanometer
1
1
8
9
v. Mis cellaneo'US 10
Ao Carbon Dioxide Concentration Meter 10
B. Schlieren Optical System 12
c. High Pressure Dew Point Indicator 1.3
n. Oil Removal 13
Figures 15
1
I. INTRODUCTION
For the purpose of developing more efficient rockets and missiles
i'or long ranges, it is necessary to acquire basic info:nnation 1n the
hypersonic Mach number range of 5 to 20. To obtain such aerodynamic
infonnation two Hypersonic Wind Tunnels, Legs No. l and Noo 2, have been
developed at GALciT. With Leg Noo 2 it is possible to obtain aerodynamic
information in one-phase air flow at a Mach number ot about 11.
During the early operation of' the Leg No. 1 tunnel at a Mach
number range of 2 to 7 it was necessary to develop various new experi
mental techniques to obtain reliable aerodynamic infozmation. The
static pressures in the test section varied in the hypersonic Mach number
range from. about 2 to ;t/4 millimeters of mere while the static
temperature was of the on:Jar of room temperature to 1100~. A great
deal or time was spent in developing manometer boards and special valves
and in perfecting new techniques for measuring these low pressures ver,r
accurately. 'lhe initial operation phase or the Leg No. l turmel was
spent in developing adequate hypersonic instrunentation i'or statio pressure,
total head, heating i'acilitles, and a stagnation temperature controller.
In this report. the important instrumentation developed over the
past i'ew years will be discussed in deta.U. The infonnation should be
usei'ul. i'or other groups planning basic research at hypersonic Mach numbers.
2
II. HYPERSONIC WIND TUNNEL DESCRIPTION
The ~ GALCIT S" x S" Hypersonic Wind 'runnels are ot the closed
return, continuouslY""''perating type and are operated altenia.taly by a
eanpressor plant consisting or sixteen compreaaors arranged in a parallel
series circu:Lt. A sd1ematio diagram or the wind tunnel installation is
shown in Fig. lA, and the control panel is shown in Fig. lBo
In operating these two tunnels, use is made or a variety ot
instrunent devices 1 some tor proper control or the compressor plant and
others tor obtaining w1ni tunnel data under properly-controlled pressures
and temperatureso In this mEillorandum is presented a brief description
ot the instrunents used at this laboratory. Several ot these have been
designed and built at the laborato~ while others are purchased items
which have been moditied tor special applications •
The use or a single compressor plant tor two wind 1llnnels has a
decided advantage over conventional methods since it decreases the shutdown
time ot the compressor plant to a min:iJnumo A portion or this shutdown
ti.me is used for maintenance and repair. During the time when one
tunnel is operating, the other, together with its associated instrument&•
tiDn, is tree tor model installation.
The two wind tunnels are referred to as Leg No. l and Leg No. 21
respectively. 'lhe pertinent characteristics and specU'ications unique
to each are described as .follows t
Ae Leg No. l, Mach Number Range 2-1
Leg No. 1, which is now operating with the nozzle blocks set .for
Mach s.a, is designed .for a maximum stagnation pressure of ~0 psi. n.
3
air ie heated to a maximum or 1tXPr during it.s passage through a steam
heat. exchanger directly att.er it.s exit. £rom the last. stage at canpreeeion.
B. Leg Noe 2, Mach Number Range 4-ll
Leg No. 21 which can be operated up to Mach ll, ha8 a maximum
stagnation pressure of lo40 ~si. The air is heated electrically to a
maximum or gooDr in the stainless steel settling chamber just. ahead of
the th:rnat.. Semi-flexible nozzle plates designed to operate over a Mach
number nmge or 1 to ll have been installed, and the nozzle 1.8 being
calibrated at. the present. timee
III. COMPRESSOR PlANT INSTRlMENTATION
A. Variable Conditions Indicated on the Control Panel
1. Inlet and OUtlet Pressures tor Each Stage of CompreBsion
'Ihese pressures are measured with standard bourdon tube pressure
gages.
2. Outlet Air Temperature tor Each Stage
The outlet. air temperature is measured with standard iron con
stantan thermocouples and recorded with a multi-point strip-chart recorder • .
3. Compression Ratio or Cert:.ain Compressor Stages
· This ratio is or interest. only men it approaches the design limit
lil.ich 1a speoitied by the compressor manutacturer. The ori tical compression
ratio 1a indicated on a duplex gage or a certain design. These gages haTe
4
two boumon mowments in one housing with their pointer sharta concentric.
'lhe movements are so chosen that the mtio of their sensitivities is
equal to the critical compression mtio of the canpress or under cons ide~
ation. With this arrangement the inlet pressure-pointer leads the outlet
pressure-pointer when the compression ratio is less than critical.
'When the two pointers coincide, the limit has been reached. This "ratio
gage" then pennits the plant operator to ootennine imnedia. tely the margin
or safety for that particular stage.
4. Stagnation Pressure
This pressure is measured with a Tate-Emery indicator which can
measure up to 1.300 psi in four ranges (described separately).
So Stagnation Temperature
Stagna t:Lon temperature is measured just ahead of the throat with
iron-constantan probes feeding into a continuously-recording controller.
B. Description of Measuring and Controlling Instruments and 'lechniques
1. · Operation of Tate-Elneey Pressure Indicator
The multiple-range Tate-Elner;y' 1s shown schematically in Fig. 2.
The operation is as followsa
Carefully regulated nitrogen (2$ psi) 1s brought into the bellows•
extending them against the action of the tension springs (S) 0 Air
pressure (P0 ) entering bouroon tube (A) detlects it together with the
attached flapper (B) in the direction shown. This cilanges the leakage
rate from oritice (C) causing the bellows (D) to collapse because ot
decreased pressure. Spring (E) is a negative position feedback fran the
bellow to the bourdon tube tlapper combination. 1he flapper tinall1'
assunes sane equilibri\U'Il position, giving a unique leak rate ancf a unique
position ot the bellows for each pressure (P 0
)o The def'onned status of
the bellows is transmitted through the rack and pinion (F am 0) 1 thus
giving a unique position ot pointer (H) on the indicator dial.
Bottled nitrogen is used to operate this indicator, thus eliminating
the need for attention to filtering and drying devices, whioh would be
necessary if' the available "house" compressed a.ir were to be used.
2o Method of Stagnation Pressure Control
Constant stagnation pressure, which is necessary for proper wind
tunnel operation, is held by means ot a differential pressure controller
of the type used in the process industries tor f'l.ow control. It is used
in the following manner (Fig. ))a
Air is pennitted to enter a pressure bottle until it is charged
to a pressure equal to the pressure at which the tunnel is to be operated.
At this time a han~ valve (V1 ) is closed, isolating this pressure, which
has been measured with the Ta te-Ernery indicator and which is to be used
as the reference pressure on one side of the controller bellowso The
air pressure to be controlled is brought to the other side of the bellows
and is compared against the reference pressure. When 'there is a pressure
di£f'erence1 the controller actuates a diaphragm-operated valve, venting
more or less air to atmosphere from the system in order to equalize the
pressure in the bellows. Pressures to 'Within .o4 psi are easily hel.d.
6
~· Air Temperature Control
a. Control for Leg Noo 1 Steam Heat -Exchanger
7.he air1 which has been dried with _silica .sel and filtered through
a series of filters consisting of activated charcoal, sintered carbon,
and a special glass filter cloth during its passage through the com
preseor plant, is then passed through the steam heat exchanger. Just
before ite entrance into the exchanger, a portion or the relatively-cool
air is bled off through a pneumatically-operated valve. 1his diverted
air is then used for finer temperature control by mixing it with the
heated air on the exit side of the heat exchanger.
'!he temperature or the final air is controlled 'by means of a
pneumatic controller incorporating both derivative and integral modes. - -The pneumatic pressure si~al from this controller is a function or the
heat input necessary to keep the stagnation temperature at a pre-set
valueo
The diaphragm valve (Fig. 4), which is actuated w.tth air pressure
from the controller and which controls the steam flow into the heat
exchanger, is connected in such a · way as to be closed with no air
pressure on its diaphragm 'WhUe the valve controll.1ng the cool and heated
air mixture ratio is normally open with no air pn!ssure on its diaphragm.
This mixing valve is also operated by the same pressure signal which
operates the steam valveo In this way they operate in opposite sense,
which d.iminishes the time constant at' the cooling portion or the oontrol
cyele. This feature is or considerable importance due to the large
themal capacity of the steam heat exchanger.
b. Control for Leg No. 2 Heatere
~e compressor plant whicll is used for the Leg No. 1 tunnel is
also used, together with its associated drying and filtering equipnent,
i'or operating the Leg No. 2 tunnel. The air 1n Leg No. 2, however, is
electrically heated 1n the stainl.ess steel pressure vessel just ahead
ot the nozzleo 'lhe same temperatum recorder-qontroller as is used 1n
7
Leg No. 1 is used to control the temperature 1n Leg No. 2. This controller
uses standard thermocouple input, giving a pneunatio signal 1n the fom
of varying pressure as the control output. 1h1s vaeying pressure from
the controller 1s t:mnsfo:r:'JIJ3d into an electrical equivalent signal by
means of a GALOll'-designed transducer (Fig. S) • The transducer consists
ol a diaphragm motor actuating, through a rack and pinion, a variable
resistor, which in tum is used to control a saturable reactor.
Stagnation tempe:mtures in Leg No. 2 have been controlled up to
9000,. ~ 10,., with the use of this control.l1ng technique.
IV. PRESSURE MEASURING MErHOOO
A. Low Pressure Silicone Mananeter Banks
Most of the pertinent pressures in the wind tunnel test section
are measured with 100 em full scale silicone manometer banks designed
and built at this laboratoeye In Fig. 6 the schematic arrangement of tM
reservoir and valving is shcnm, and Figo 7 shows the manometer board.
'l'h1s is a standard reservoir type manometer using the GAWI'l'-design,
three-way- vac\lUtll valve (Fig. 8). When no pressure readingS are l:eing
taken, the valve is in such a position as to expose the liquid column
8
to the same low pressure as the reservoiro ibis reserY'oir pressure is
kept at between 3 and 10 microns ot mercury pressure and 1s checked
regularly' by means of an ionization pressure gage called the "Alphatron•o
This keeps the silicone nuid under continuous vacuum, which is necessar.r
in omer to prevent air from becoming dissolved into the liquido When
pressure readings are to be taken, the valve is adjusted to the position
shown in the figure, which exposes the liquid column to the pressure
being .aasured (Fig. 6).
The silicone liquid used in the manometers is known commercial.ly
as Dow Coming Compound 200e For this application a viscosity rating o.t
10 centistokes is used.
B. Low Pressure Micrananometer Bank
A twelve-tube micromanometer bank has been designed am bullt .tor
pressure readings which require accuracies greater than .2 nun of silicone
(Fig. 9). ibis micromanometer is capable of sensitivity in the order of
.ooS JID1l of silicone. This sensitivity is attained by projecting an
image of the meniscus in the glass tube onto a ground glass viewing
screen, on lbich there is scribed a horizontal index line. The men1sC\l8
and the index line are superimposed by adjusting the elevation of the
projection system by means o.t a moto~ri ved precision lead screw. This
elevation is then read from. the counter, which is geared to the lead
screw to read directly' in incrementa of .01 tnnt. ibe full range of the
micromanometer is 30 em.
In order to improve visibility the a1licone nuid 1s dyed a blue
color by passing it through filter paper on which is sprinkled dye
(Calco oil blue, ZA ex oono. from the American Cyanamide Co., Calco
Chemical Division, Dyestui'f l>epartmmt, Boundbrook1 New Jersey).
c. Tilting "U" Tube Micrananometer
A micromanometer w1 th a range ot one inch has been developed•
This Wlit can use either silicone or mercury with a sensitivity ot ! .oooS in.
(Fig. lO). It is essentially a "U" tube with short legs, which can be
tUted about the pivot (P) by means of a machinist's micrometer head
(M). The manner of operation is as follawsa
Stopcock (S) is tUl"Dad to the position which exposes both liquid
columns to the reference plt!ssure. At this time the micrometer is
adjusted to the "null" posi tion1 which is indicated at the suri'ace ot
the fluid by a distorlion of the reflected light (L). This distortion
i.e caused when the point of the "catwisker" pierces the meniscus ot the
manometer fiuide 'lhis "piercing point• is quite definite and can be
repeated to within .oooS inche This "null" posi ttcm of the micrometer
1s recorded as the ntference level. The stopcock is then turned to the
altemate position \tlich exposes the liquid colUmns to the reference and
the unknown pressure, respectively. The micrometer is again adjusted for
the new nullo The difference in micraneter readings gives the head (h)
of manometer liquid. (.oooS in. of silicone 1s equivalent to oB microns
of me rcur;y •)
10
V • MISCELLANEOUS
Ao Carbon Dioxide Concentration Meter
Since carbon dioxide acts as a nucleant tor air condensation when
it ie present in quantities greater than a certain critical amount1, it
ia of interest to monitor the co2 concentration,, particularly in Leg No.
2, 'Where it could possibly build Up due to the burning of small oU
particles as they pass through the electrical heater vhUe being carried
through the air stream fran. the compressor plant. With this in mind a
continuously-sampling a~er vas designed and built. (Fig. 11)
Operation of this analyzer is based on the fact that the quantity
of carbon dioxide dissolved in water is proportional to its partial
pressure in the gas mixture to be analj"zed.
'Wh.ere
co • 2 22.4
co2 • concentration of dissolved carbon dioxide
p co2
• partial pressure of carbon dioxide in atmosphere
Carbon dioxide -bicarbonate equilibrium reactiont
To measure the hydrogen ion (ph) concentration an indicator ia
tiSed 1n the solution, in this case bromo-teymol blue. The color range
of this indica tor is trm yellow on the acidic side to deep blue on the
1. "Effects of Impurities on the Supersaturation of Nitrogen in a Hypersonic Nozzle", by' P. D. Arthur and Ho To Nagamatsu, GALCIT ~arsonic Wind Tunnel Memorandum No. 1, March 1, 1952.
u
basic. 'l'he ph or the indicating solution is adjusted, before measurementa
are taken, to tall sanewhere between the two extremes, that is, men the
bromo-t~ol blue appeare greenisho The~ ~ust.ing a elutions
used are very dllute solutions or hydrochloric acid and sodium hydroxide
and. are made while either the standard air or sample air is bubbled
through the solution.
When equUibrium has been reached, an approximately equal amount
is poured 1nw the bubbling cells, 1n 1his case consisting o! two
pyrex test tubes.
'lbe detennination ie made ae tollowsa With Valve 3 opened to
pennit the standard. air to bubble through one ot the cells and Valve 2
opened to bubble the sample · air through the other cell, an observation 1s
made or the colors or the solution. With sample air containing a greater
percentage of co2
than the standard air, there will be brought about a
color mismatch. Valve l is then adjusted untU the sample air is
properly diluted to bring about a color balance. From the calibrated
!lowmeters a ratio or dilution can be secured. With this ratio and the
known concentration or carbon dioxide 1n the standard. air, the concentra
tion in the sample air can be computed.
The standard air can be made up tor special concentrations, or
ominary outdoor atmospheric air can be used tor measur.t.ng in the mnge
of .o)% concentration or co2• Many investigawrs have found outdoor
atmospheric air to contain between o03l and .032% carbon dioxide, this
figure being constant over various part.s or the country.
It has not been dif'ticult to sense 70 parts per million of co2
with visua1 color canparison in the test tube cells. '1h18 represents
approximately .1 ph change. Obvious~, when more sensi t.ivity ie required,
12
other methods of ph measurement are required, that 181 precision optical
and photoelectric colormeters and electronic ph metei'IJ"
Bo Schlieren · Optical System
'l'he schlieren system is a conventional 11 Z" configuration with
traversing nate which can be controlled from the camera sight, (Ffg. 12).
This pennits rapid monitoring of the complete length of the test section
through a series of glass ports which are spaced at regular intervale on
the sidewalls •
The pertinent specifications of the schlieren system are as
tollowst
Spherical Mirrors
f.lo 120 inches surface t 1./4 ~ dia. 8 inches
Flats
Lamp
surface t 1./4 " dia. 12 inches
General Electric BH-6 high pressure mercury vapor air cooled
Slit Size
l tTIIl x S tTIIl (nominal)
Film Size
4" X 5"
Shutter Speed Range Available
1./400 sec •••••••• 1 sec.
13
o. High _Pressure 11ew Point Indicator
The dew point indicator show in Fig. 13 baa been designed for
Measuring the dew point at air at pressures up to 1000 psio · It is of
conventional design using the cooling e.f'fect of carbon dioxide which is
expanded against the rear of a chromium-plated ndrror. The temperature
of this button is read at the tilTle that dew deposit 1s observed through
the window. \tlt1h the t91Tlperature and pressure known, the specific
humidity can be computed or read directly off the c~rt (Fig. 14).
Do Oil &moval
During the nonnal operation or the canpressor plant which is
used for operating the 'bro wind tunnels, oil or the order of 1 quart per
hour is added to the air e tream. Removal or this large amount of oil 1s
accomplished by a series of different types of filters.
After each compressor there is a vortex type or .filter, commonly
called a cyclone separator, which ·removes the largest part of the oil.
Next, all or the air passes through an impingeMent filt.er made up of
~anisters filled with absorptive, activated charcoal (cocoanut shell),
which also removes oil vapom. It is believed that the oil at this point
is in the fonn of droplets, and the air is passed through two different
porosities of sintered carbon blocks* 1" thick1 which take out drops over
10 microns in diameter.
The final stage of filtering is done by a corrmerical.l.y-manufactured
fiberglass paper manufactured by the Mine Safety Appliances Compaey•**
* National Carbon Company, 30 East 42nd Street, New Yorlc 17, N. Yo
** Mine Safety Appliances Company, Braddock~ Thomas~ and Meade Streets, Pittsburgh 8, Pennsylvania0
The Mo Sa Ao filter, called "Ultra-Air Space Filter", comes as a unit
read7 tor installation. This filter 1B unconditionally guaranteed to
be 99.9S% effective against particles .3 micron 1n diameter with a
pressure drop of l inch of water. It has been 1n use at this laborato17
for one year, passing 6o pounds of air per minute at a velocLty ot 55 rt.
per minute and has required only three washings to date. lhese washings,
using carbon tetrachloride, were cbne when a pressure drop of two inches
of water was indicated across the filter.
I I I I I
L----..g-----J
2.
LEG NO.I
LEG N0.2 TEST SECTIONS
~.
L ____ j _____ ~~-~~~~------J
':1 v 1
SCHEMATIC DIAGRAM
STEAM HEATER
s
OF GALCIT 5x5in . HYPERSONIC WIND TUNNEL INSTALLATION
FIG. lA
DROPLET FILTER
6
3 VAL.l/ES
a MOTORS
• COMPRESSORS
-~ 7
~
'i ~ ~fwlr.. TJ.. (Q
f!.w r Ov ci- 1 ) •v.io!fn, ,.(lfh.t..i. c~d ,
E
-D·BELLOWS
NITROGEN
SCHEMATIC OF TATE-EMERY PRESSURE INDICATOR
FIG. 2
17
P.
Po
TATE-EMERY
V1-HAND VALVE
DIFFERENTIAL PRESSURE CONTROu.ER
PRESSURE BOTTLE (Rated 2400 psil
TO
DIAPHRAGM VALVE INSTRUMENT AIR (STAGNATION VENT)
SCHEMATIC OF STAGNATION PRESSURE CONTROL METHOD
FIG. 3 ~
~~
L.c::: COOL AIR
~ .z-~~" ((-:! . J:)L
~r--
' ~~ \.\(ffi~
~ STEAM HEAT EXCHANGER~
-Lbtl
TEMPERATURE 7 CONTROLLER
®
\_;I ~ '[[Jr-DIAPHRAGM VALVE
NORMALLY OPEN b.-., HEATED AIR
j DIAPHRAGM VALVE II CO~DENSATE NORMALLY CLOSED OUT
l
CONTROL AIR LINE
:;> 16) 01==~ INSTRUMENT AIR
SCHEMATIC OF LEG NO. l TEMPERATURE CONTROL FIG. 4
':) ~· I
STEAM IN b..J ~
AIR
IN
300 KVA MAXIMUM
•
CONTROLLER
DC SATURATING 3-PHASE I CURRENT CHASSIS
SATURABLE REACTOR
HELl POT
O}}»k«dih. HEATING GRIDS
ELECTRICAL HEATER SHELL
SCHEMATIC OF LEG NO. 2 HEATER CONTROL
FIG.5
0, c*
INSTRUMENTAIR
THERMOCOUPLE PROBE
~
TO TUNNEL
TO ALPHATRON
TO VACUUM PUMP
RESERVOIR FOR SILICONE
MANIFOLD
GALCIT 3·WAY VACUUM VALVE
READING TUBE
REFERENCE TUBE
SCHEMATIC OF SILICONE MANOMETER FIG: 6
21
r
FID.7
NAN<l-1E'IER BOARD
Fm. 8
IJJW PRESSURE VALVES
22
23
r t l .. . . ' ' ' ~ \
.. . \ \ . " . \ \ .. . • . ., \ \ \
. '•
~ . . \ \
. . ·., \ ~\ '" .... ,, ....
·~ .. .. ~\
~ ' 1( ·~
FIG. 9
12-TUBE MIC l{)MAtnlE TER BANK
REFERENCE PRESSURE
NKNOWN PRESSURE
GLASS CATWHISKER (C)
HIGH VACUUM, MERCURY SEAL STOPCOCK
(S)
MICROMETER HEAD {M)
SCHEMATlC OF TILTING U-TUBE MICROMANOMETER
FIG. 10 t?-
FLOWMETER
UNKNOWN AIR SAMPLE
0
NEEDLE VALVE NO. 3
FLOWMETER
BUBBLING . CELLS
NO. I
NITROGEN {FREE OF C02 )
CARBON OIOXI DE CONCENTRATION METER
FIG. II
1\) \J'l
ACHROMAT ,..--LAMP
r---12 11 FLAT
a• SPHERICAL MIRROR
I - 8" SPHERICAL MIRROR I I
N _ _ -r - -~ j _________ ill:2::~:==:::::=--l ,, I ' ' ',,-.) __ -- - : ""\.
'->
SCHEMATIC OF SCHLIEREN SYSTEM FIG. 12
\\_SHUTTER
\_KNIFE EDGE
VIEWING SCREEN a CAMERA
&;
VALVE NEEDLE
SAMPLE AIR .,
SEAL
MIRROR BUTTON
SCHEMATIC OF HIGH PRESSURE DEW POINT INDICATOR
FIG. 13
PIN
N ~
>-1-0 -:E :::>
---DEW POINT --FROST POINT
psig J4.7-;-, 50
100 150
I 200 :)f'\ \ \:;.,-4 ......,..,.,..........-~,...;.............:::;:::>' 1~1 I I ~ ~
:I:I0-4 1 I .- ..c1 r..c ..:;;.~ -:::;-e: ~~ "F .,......- I I 7 7 / >'_/"/=~ .>-~ :.;;r :,;7
(.)
u. (.) w a.. (/)
300 ·-400
.~ I \ \l~~g +----------4
-40 -20 0 20 40 60 TEMPERATURE (°F)
SPECIFIC HUMIDITY VS. DEW POINT TEMPERATURE AT VARIOUS PRESSURE LEVELS
FIG. 14
80
N (X)
CALIFORNIA INSTI'J.Ul'E CF TECHNOIOOY HYPERSONIC WIND TUNNEL
CONTRACT NO. DA-d.J-495~rd-19
REPORl' DlSTRIBUTION LJBT
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Distribution List
u. s. Naval Inspector ot Ordnance Applied Physics Laboratory Johns Hopkins University 8621. Georgia Avenue · Silver Spring, Maryland
Mro Bernard F. Jaeger Head, Ac rodyna:nics Branch u. s. Naval Ordnance Test Station Inyokern China Lake, Cal.ii'omia
Conunander Western Development Division Post Office Box 262 Inglewood, California
Armed Services Technical Information Agency (5 Copies)
Document Service Center Knott Building Dayton 2, Ohio AT'l'EHTIO!l : I:SC-8D22
National Advisory Cormdttee for Aeronautics 1512 H Street, Northwest Washington 25, D. c. ATTENTION: Aerodynamics Branch
Mr. John Stack Associate Director of Research National Advisory Conunittee for Aeronautics Langley Memorial Aeronautical Laboratory Langley Field, Virginia
Dr. John c. Evvard National Advisory Committee for Aeronautics Supersonic Propulsion Division Lewis Flight Propulsion Laboratory Cleveland, Ohio
Mr. H. Julian Allen National Advisory Conunittee for Aeronautics Ames Aeronautical Laboratory l1offett Field, Cali.forraa
Library Institute of the Aeronautical Sciences 2 East 64th Street New York 21, N. Yo
ARO, Inc. Post Office Box 162 Tullahoma, Tennessee
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General Electric Company Reports and Docunents Division 2900 Campbell Avenue Schenectady 5, New Yolk
Ramo~ooldridge Corporation 8820 Bellanca Avenue Los Angeles 45, California
RAND Corporation 1700 Main Street Santa Monica, California ATTEtiTION: Miss Hargaret Anderson,
Librarian
Sverdrup and Parcel, Inco Syndicate Trust Building St. Louis 11 Missouri
Mr. E. E. Clai'k Chief of Aerodynamics Glenn L. Martin Company Baltimore 3, Maryland
Hr. A. Flax Head, Aerodynamics Research Department Cornell Aeronautical Laboratory, Inc. 4455 Genesse Street Buffalo 21, New York
Mr. Martin Go land Director for Engineering Sciences Midvrest Research Institute 4049 Pennsylvania Kansas City 11, Hissouri
Dr. Henry To Nagamatsu General E)e ctric Company Research Laboratory Schenectady, New York
Dr. Allen E. Puckett Hughes Aircrai't Company Culver City, California
Hr. E. Williams RAiiD Corporation Hissile Aerodynamics Section 1700 Main Street Santa Monica, California
Distribution List
Professor Harold o. Barthel University of D.l.inois Aeronautical Institute Urbana, Illinois
Professol' R. c. Binder Pumue University Laf'ayette, Indiana
Professor L. M. K. Boelter University of California Engil1eering Department Los .Angeles 1 California
Dr. Seymour H. Bogdonort Princeton University Department of Aeronautical Engineering Princeton, New Jersey
Professor Sin-I Cheng Princeton University Depart.ment of Aeronautical Engineering Princeton, New Jersey
Professor Francis Clausal' Johns Hopkins University Graduate School of AeronautiC& Baltimore, Maryland
Dro R. Courant New York ·University New Yorlc, No Y.
Profesao r Ho W • &Intone Harvard University Department or Applied Physics Cambridge 38, Massachusetts
Professor R. J o Emrich Lehigh University Department of Physics Bethlehem, Pennsylvania
Professor Antonio Ferri Polytechnio Institute of Brooklyn Ae J.'Odynamics Labo ra.toty 527 Atlantic Avenue Freeport, New Yorlc
Dr. R. G. Folsan Director, Engineering Research Institute East Engineering Building Uni-versity or Michigan Ann Artx>r, Michigan
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Dr. R. Paul Harrington Rensselaer Polytechnic Institute Aeronautics Department Troy 1 New York
Dr. ~olph Hennann Department of Aeronautical Engineexlng University or Minnesota Minneapolis l4, Minnesota
Professor A. M. Kuethe University of' Michigan Aeronautics Department Ann Arbor, Michigan
Dr. Ting-Yi Li Rensselaer Polytechnic Institute Aeronautics Department Troy, New Yortt
Dr. c. c. Lin Department of Mathematics ~mssachusetts Institute or Zachnology Cambridge, Massachusetts
Professors. Io Pa1 Institute of Fluid Dynamics and
Applied Mathanatics University of Maryland College Park, MarylaM
Dr. Ronald F o Probstein Brown University Division or Engineering Providence, Ro I.
Dr. s. A. Schaaf Associate Professor or Eng. Sciences Low Pressures Research, Inste ot &lg. Bee. Engineering Field Station 1.301 South 46th Street Richmond, California
Dr. w. R. Sears Cornell University Graduate Sehool of Aero. Fngineer'ire Ithaca, New York
Professor H. Guyf"onl Stever Massachusetts Institum of Technology Aeronautical Phgineering Department Cambridge, Massachusetts
Professor Ro G. Stoner fennsylvania State University !'hyaics Department State College, PennsylTania
Distribution List
Dr. M. J" Thompson Defense Research Laboratory University of Texas Post Office Box 8029 Austin 12, Texas
Professor Gavin L. von Eschen Ohio State University Aeronautics Department Columbus 12, Ohio
Dr. Th. von K!rm!n 1501 South Marengo Avenue Pasadena 5, Califor.nia
Jet PropulB ion Laboratory Californi a Institute of Technology 4800 Oak Grove Drive Pasadena 2, Califo mia AT 'IEN.l'ION 1 Reports Group
Dr. P. \vegener Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove . Drive Pasadena 2, California
Dr. H. s. Tsien Jet Propulsion Center California Institute of T
8chnology
Pasadena 4, California
Aeronautics Librar.y California Institute of Technology
Dr. Clark B. Millikan (2 Copies) Dro Julian D. Cole Dr. Donald E. Coles Dr. P. A. Lagerstrom Professor Lester Lees Dr o H. W. Lie}Illa.nn Dr. A. Roahko California Institute of Technology
Hypersonic Design Group Hypersonic Experimental Group Hypersonic Theoretical Group Hypersonic File California Institute of Technology
TOTAL • 82
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