Experimental facilities at T.C.E.A.

(1)

v

TRAINING CENTER FOR EXPERIMENTAL AERODYNAMICS

Technica1

Me~orandum

II

EXPERIMENTAL FACILITIES AT T.C.E.A.

by

R.H. Korkegi

RHODE.-SAINT-GENESE. BELGIUM

(2)

(3)

Technica1 Memorandum 11

EXPERIMENTAL FACILITIES AT T.C.E.A.

by

R.H. Korkegi

(4)

(5)

INTRODUCTION

LOW-SPEED WIND TUNNELS Composite Wind Tunnel L-l

Wind Tunnel L-2 Wind Tunnel L-3 Wind Tunnel L-4

SUPERSONIC AND TRANSONIC WIND TUNNELS Continuous Supersonic Wind Tunnel S-l

Supersonic Wind Tunnel S-2 Blow-Down Wind Tunnel S-3 Transonic Wind Tunnel T-2

HYPERSONIC W 11+& 'TUNNELS Intermittent Hypersonic Wind Tunnel H-l Blow-Down Hypersonic Wind Tunnel H-2

TURBOMACHINERY LABORATORY Low-Speed Cascade Tunnel C-l

Low-Speed Rotor Test Stand R-l Water Compressor R-3

High-Speed rotor Test Stand R-2

OTHER EXPERIMENTAL FACILITIES Shock Tube Water Table ELECTRONICS LABQRATORY FUTURE PLANS REFERENCES FIGURES Page l. 2. 2. 3. 3. 3. 4. 4. 5. 5. 6. 6. 7. 8. 9. 10. 10. 11. 11. '( 12. 12. 12. 13. 13. 15. 16.

(6)

(7)

The purpose of this note is to provide, in one document, a

description of all the existing facilities, together with a brief statement of plans for the immediate future.

INTRODUCTION

The Training Center for Experimental Aerodynamics has an extensive range of facilities in support of its academic program. The facilities include several low-speed and supersonic wind tunnels, a transonic test section, hypersonic wind tunnels (now being installed), turbomachinery, a small shock tube, a water table, and a well-equipped electronics laboratory. A plan of the laboratory showing the location of these facilities is given

in Figure 1.

When the hypersonic wind tunnels become operational (expected in the course of 1962), the range of speed will extend from low speeds to a Mach number of approximately 8. No further extension of the Mach number range with classical type intermittent facilities is planned.

As the activities of T.C.E.A. are primarily academie, and there are at present no facilities in which real-gas phenomena can be studied, it is intended that new equipment should comprise same high-teQllu~,~aturé., l.ow daris'i;ty :,devices of modest size.

(8)

2.

LOW-SPEED WIND TUNNELS

There are four low-speed wind tunnels refered to as L-l, L-2, L-3, and L-4, in operation at T.C.E.A. The largest and most important of these facilities is the composite wind tunnel L-1.

Composite wind tunnel L-1

The low-speed wind tunnel L-l,completed in 1950, has a c1osed-return and is of unusual design in that it can be operated in any one of three configurations :

1) with an open jet of 3 m diameter with a maximum airspeed of 60 m/sec 2) with a c10sed working section of 2 m diameter w1th a maximum airspeed

of 100 m/sec

3) with a vertica1 jet of 3 m diameter for spin testing with a maximum air speed of 30

mi

sec.

The contrarotating fans of this faci1ity are driven by a 580 KW DC motor.

A six-component mechanical beam ba1ance is provided for force and moment measurements. A 10

m3

(350 ft3 ), 15 ATA air storage r.eservoir and an automatic pressure regulating system are avai1ab1e for tests requiring a high-pressure air supply, as, for instance, for applications of boundary-layer control.

Wind tunnel L-l is extensively used for non-aeronautical tests as well as for course work and student projects.

Plan and elevation views of wind tunnel L-1 are shawn in Figures:' 2a ·.and.'b~ailarà detai.l~tFdes.é::siptton is 'given' in Ref. 1.

(9)

Wind Tunnel L-2

Wind tunnel L-2~built at T.C.E.A. in 1958,has a closed working section 30 cm (12 in) in diameter and an open circuit but is essentially a 1/1 scale model of tunnel L-l in the closed-jet configuration. lts fan is driven by a 6 HP DC motor, and the tunnel can be operated at air speeds up to 50 m/sec (165 fps).

Wind Tunnel L-3

Originally built as an exhibit for the International Air Show at Bierset (Liège), Belgium, in June 1958, wind tunnel L-3 is a 1/20 scale model of wind tunnel L-l in its open jet configuration.

A maximum air speed of 8 m/sec (26 fps) can be obtained in its 15 cm diameter (6 in) working section.

It is used for low speed instrumentation work (e.g. hot wire anemometry).

Wind Tunnel L-4

L-4 is an open-circuit wind tunnel with a closed working section 20 cm (8 in) in diameter. lts axial-flow fan is driven by a 75 HP De motor, and airspeeds up to 120 m/sec (400 fps) can be obtained. It is mainly used for the development and calibration of ,flow-survey instruments for low speed turbomachinery and, as such, is located in the turbomachinery labora-tory.

(10)

4.

8UPER80NIC AND TRANSONIC WIND TUNNELS

Three supersonic wind tunnels, S-l, 8-2, and S-3, are in operatinn at T.C.E.A. An alternative transonic test section, T-l, is available for wind tunnel 8-1.

In addition, a transonic wind tunnel, T-2, made available to T.C.E.A. by the Aeronautical Research Laboratory of the Wright Air Development Center, U.S.A., is expected to be installed in the near

future.

Continuous Supersonic Wind Tunnel 8-1

8-1, built in 1950, is a continuous, closed return variable-density, supersonic wind tunnel of the Ackeret type.

It bas a 40 x 40 cm (16 in x 16 in) test section and can be operated at Mach numbers up to 2.5.

It is driven by a 13-stage axial flow compressor powered by a 615 KW DC motor. Owing to its small power, the wind tunnel is operated at sub-atmospheric stagnation pressures (0.1 to 0.3 ATA).

A silicagel dryer maintains the humidity level of the air during a run below 2 parts in 10,000 at a stagnation pressure as low as 0.1 ATA.

Test sections for supersonic and transonic testing are available. They are followed by a variable geometry diffuser incorporating a model

support mechanism allowing axial and vertical translation, and variable incidence. The tunnel is equipped with an optical system-for shadowand Schlieren flow visualization.

(11)

,-For supersonic operation, fixed-geometry metàl nozzle blocks, coated wtth araldite, and designed for a Mach number of 2.25 are used.

A transonic test section,'T-l, designed by the NASA, was built by T.e.E.A. in 1958. It has top and bot tom slotted walls and solid side walls, and covers a range from subsonic speeds to a Mach number of approxi-mately 1.2.

A view of wind tunnel S-l is shown in Figure 4 and a detailed description is given in Ref. 2.

Supersonic Wind Tunnel S-2

The small continuous supersonic wind tunnel S-2 has a 1.5 cm x 1.5 cm (0.6 in x 0.6 in) test section originally built as an exhibit for the International Air Show at Bierset (Liège), Be1gium, in June 1958.

There are two nozzle blocks for Mach numbers of 15. and 2.2 respectively.

S-2 is a non-return, suction-type tURnel. It takes in atmospheric air through the silicagel dryer of wind tunnel S-l, and us es the latter's vacuum pump for the drive. This tunnel has an independent Schlieren system.

Blow-down Wind Tunnel S-3

The supersonic blow-down wind tunnel S-3 has a 5 cm x 6 cm

(2 in x 2.4 in) test section fitted with a half nozzle designed for a Mach number of 2.75. It is driven from 10 hLgh pressure air reservoirs with a total capacity of 4.4

m2

(155 ft3) at 40 ATA, and exhausts to the atmosphere.

The reservoirs are pumped up from atmospheric pressure to 40 ATA in 6 hours by a two-stage 7 KW reciprocating compressor through a silicagel

(12)

6.

dryer and a filter.

The available running time of wind tunnel S-3 at a stagnation pressure of

4

to 6 ATA is approximately 2 minutes.

This facility is provided with a Schlieren system mounted on a mobile horizontal frame supported on rails to allow axial scanning of the complete test section (approximately 30 cm or 12 in).

A view of tunnel S-3 is shown in F~gure 5.

Transonic Wind Tunnel T-2

T-2, made available to T.C.E.A. by the U.S. Government, is a

closed return transonic wind ~unnel with a slptted-wall, circular test

section 6 in (15 cm)' :i.n diameter. It is to be driven by wo 5350 C.F.M.

(150 ~/min) centrifugal blowers requiring wo 125 HP motors. The

install-ation of this faci1ity is in the planning stage. The purpose of T-2 wil1 be to re1ievé tunnél 8-1 of transonic testing (with the transonic test section T-l) in the academic program.

HYPERSONIC WIND TUNNELS'

Two intermittent hypersonic wind tunnels have been designed at T.C.E.A. Wind tunnel H-l is expected to be in operation.:in 1962, and wind tunnel H-2, of small siza and modest Mach Qumber, is undergoing

(13)

Intermittent Hypersonic Wind Tunnel H-l

The intermittent hypersonic tunnel H-1 has a 12 cm x 12 cm (5 in x 5 in) test section and is designed to cover a Mach number range from 4 to 8 at stagnation pressures up to 35 atm. and stagnation tempera-tures up to 500°

e

(1400° R), with running times of 1 to 3 minutes.

The tunnel will be fed from two existing high pressure air reservoirs with a total capacity of 60 m3 (2100 ft 3) at 40 atmospheres. Suction by means of a supersonic ejector is provided in the tunnel diffuser in order to achieve the high pressure ratios necessary for operation at Mach numbers of 6 and above. The ejector is to be fed from the same air

supply as the tunnel circuit.

Heating of the tunnel air will be achieved by means of a storage heater consisting of a bed of 2 tons of ferro-silicon pebbles contained in an internally insulated steel shell. The pebbles will be pre-heated prior to a run by means of an auxiliary electric heater and blower system. An automatic pressure regulatirtg valve will maintain constant pressure during a run.

Typical estimated operating characteristics are as follows:

Mach number M 5 6 7 8

Stagnation pressure Po (atm) 17 30* 30* 30* Stagnation temperature _To (Oe) 120 230 350 500

Weight flow W (Kg/sec) 2.0 1.5 0.80 0.35

Reynolds number per cm Re/cm x 10-6 • 0.28 0.22 0.10 0.055

Running time t(min) 1 1 1/2 2 1/2 2

* with ejector.

Two pairs of nozzle blocks are available:

contour blocks for M

=

5.3, and wedge tilt blocks which cover the range

(14)

8.

Instrumentation will include a Schlieren optical system, fast response pressure and temperature measurement and recording equipment, and a continuous record of stagnation pressure and temperatures. Tunnel

controls and indicating and recording instrumentation will be mounted in a control console to be housed in a sound-proof cabin.

The complete test section was made avai1ab1e to T.C.E.A. by the U.S. Nava1 Ordnance Laboratory, White Oak, Mary1and.

The construction of this facility (excluding the high pressure air supp1y) and its instrumentation are who1ly subsidized by the U.S. Government through a contract monitored by the European Office of the Office of Aerospace Research.

The hypersonic tunnel circuit is expected to be instalied by the end of 1961.

Housing for the 125 HP compressor plant to fil1 up the high pressure air reservoirs, as weIl as the dryer unit have stiil to be completed.

Views in plan and elevation of the hypersonic tunnel are shown in Figures 6a and 6b.

Blow-down Hypersonic Wind Tunnel H-2

The small hypersonic wind tunnel H-2 with a conical nozzle and 4 cm (1.6 in) diameter test section designed for a Mach nlllnber between 5.5 and 6, was started as a student project (Ref. 4).

It is fed from the small 40 ATA air ~upply described under S-3 and exhausts to the atmosphere.

(15)

A storage heater consisting of 33 Kg (72.5 lbs) of aluminium

pebb1es can raise the air temperature to 2000

C (3900

F). A centrifuga1 blower and a 2.5 KW electric resistance heater in open circuit with the

storage heater, serve to pre-heat the pebb1es. Performance tests with a

dummy storage heater were carried out as a student project (Ref. 5).

A Sch1ieren system is being designed for this facility. The running time is expected to be between 1 and 2 minutes.

This faci1ity was constructed and installed in the late Spring of 1961, and is expected to be operationa1 before the end of 1961.

TURBOMACHINERY LABORATORY

The turbomachinery laboratory was active1y started in 1960 with several faci1itiesformer1y in operation at the NASA Lang1ey Research Center and made avai1ab1e to T.C.E.A. by the U.S. Government.

Extensive modifications of the building housing these faci1ities and the e1ectrica1 power supp1y were underwritten by the Belgian Government.

The faci1ities inc1ude a low speed cascade tunnel, C-l, a low speed and a high speed rotor test stand, R-1 and R-2 respective1y, and a low speed tunnel for instrument ca1ibration, L-4 which is described elsewhere in this report.

In addition, a water compressor, R-3, was recently made' avai1able

to T.C.E.A. by the Fluid Dynamd~s Research Laboratory at Wright-Patterson

Air Force Base, U.S.A, It has been overhau1ed, and is expected to be

(16)

10.

A full description of the turbomachinery equipment is given in Ref. 3.

Low-speed Cascade Tunnel c-l

The tow speed cascade tunnel has a rectangular test section 5 in x 20 in (12 cm x 50 cm) in an open return circuit. and is driven by

a centrifugal blower powered by a 25 HP

oe

motor. The maximum airspeed is

130 ft/ sec (40

mi

sec).

The test section is equipped for porous wall suction and also has slits for boundary layer removal upstream of the row of blades to be tested.

This facility, in operation since early 1960, is used for studies

of blade section~,and primary and secondary flows in cascade.

Cascade tunnel C-l is shown in Figure 7.

Low-speed Rotor Test Stand R-l

R-l is an open circuit facility with atmospheric intake and

exhaust. lts rotor bas a tip diameter of 28 in (70 cm), and a hub diameter

of 22 in (56 cm). It is driven by a 75 HP DC motor and has a maximum tip

speed of 440 ftl sec (135

mi

sec). This facility bas been in use since

early 1960 for the study of low-speed compressor rotor performance. It is

planned to modify R-l by the addition of inlet guidevanes and a stator to allow the study of a complete stage.

(17)

Water Compressor R-3

R-3 consists of a three-stase axial flow pump using water as a working fluid in a closed return circuit. The three stages have equal

dimensions with a hub diameter of 8.3 in (21 cm) and a tip diameter of 11.4 in (29 cm). The pump is driven by a 2 HP variable speed DC motor and has a maximum r.pom. of 400. This facility is used for the visualization of flow phenomena in axial-flow turbomachinery.

Made available to T.C.E.A. by the U.S. Government, R-3 has been overhauled, and it is expected to develop the required instrumentation, install it and put it in operatinn during the academic year 1961-1962.

High Speed Rotor Test Stand R-2

The high speed rotor test stand is a closed return, variable density facility which can be operated with gases other than air. It has a single stage with a rotor whose tip diameter is 16 in (40 cm) and hub diameter 12 in (30 cm), operating at a maximum tip speed of 1000 ft/sec

(300 m/sec) corresponding to 17,500 r.p.m.

It is driven by a 250 HP DC motor.

This faci1ity has been in operation since the end of 1960, and is used to gain basic information on axia1 flow compressors in compressi-b1e flow and to study the mechanism of three-dimensiona1 losses in heavily loaded blading.

(18)

OTHER EXPERIMENTAL FACILITIES

In addition to the facilities mentioned above, a small shock tube and a water table were designed and built as student projects.

The shock tube whose design is described in reference 6, has a circular cross-section 10 cm (4 in) in diameter, a high pr~ssure chamber 1.05 m (41 in) long, and a low pressure chamber of 3.25 m (128 in). Air is used at pressures up to 10 ATA on the high pressure side, and down to 1 mm Hg on the low pressure side. Fast response instrumentation development for the shock tube has been the object of several student projects

(references 7 and 8 for example). Thin film resistance thermometers and baryum titanate pressure transducers and attendant circuitry have been developed and used to measure shock velocity and shock strength.

The shock tube is shown in Figure 10.

The free surface water table is used for hydraulic analogy to two-dimensional compressible f1ows. It has a test section of width 0.86 m (34 in) and length 1.50 m (51 in), with a clear glass floor for flow visua-1ization. Water flow is maintained by means of a pump in a closed circuit. The essential instrumentation consists in a micrometric depth gauge for quantitative;neasurements and a shadowgraph system used to visualize surface waves a sample of which is shown in Figure 11.

Although the water table is a device which was developed many years ago, and the analogy has many limitations, it repres~nts a useful, simple tool for academie purposes. The present one was designed by students and has lent itself to several student projects an example of which is given in Ref. 9.

(19)

ELECTRONICS LABORATORY

The electronics laboratory was extensively built up since the

creation of T.C.E.A~ for the purpose of developing electronic

instrument-ation and equipment associatedwith aerodynamic testing.

Besides standard electron~instruments, the laboratory has a

small analog computer, has deve10ped strain-gauges balances and a"

calibration rig, and equipment for measuring osci1latory derivatives.

The present trend of work in the laboratory has been toward

,

fast response instrumentation in keeping with the requirements of experi-mental facilities with very short running times.

A view of the electronics laboratory isshown in Figure 12.

FUTURE PLANS

With the completion of hypersonic wind tunnel H-l, T.C.E.A. will be equipped with a wide range of facilities covering the spectrum

from low speeds to a Mach number of 8, along with turbomachinery, a shock tube and a water table, in support of its academic program.

With current developments in aerodynamics in the direction of hypersonic, or hypervelocity flight, and the re-entry problem, real gas effects associated with very high local air temperatures, and low density flows have taken on increasing importance, and the study of these phenomena should form an integral part of a well-balancedacademic program in experi-mental aerodynamics, and more genera1ly, in gas dynamics.

(20)

14.

As such, plans for the immediate future at T.C.E.A. are to develop a facility yielding sufficiently high temperatures and moderately low densities so that real gas effects are important. With the exception of the plasma tunnel, high temperature facilities currently in use or in development elsewhere are generally of the energy discharge type -- shock tubes and tunne~ gun tunnels, electric arc driven tunnels -- with extremely short running times (a small fraction of a second).

In reviewing these various types of facilities within the scope of the academie and research work.in being and contemplated at T.C.E.A.

(studies of the physics of gases and basic gas dynamic phenomena), the plasma tunnel, offering the possibility of long running times, appears to be best suited.

The type of facility contemplated would be flexible and of modest size, with a plasma heater of the order of 20-or 50 KW coupled with a pumping system capable of evacuating the test chamber to pressures of the order of 10 microns. Such a facility could operate at hypersonic Mach numbers and high stagnation enthalpies inspite of low power since the mass flow would be very small. It would lend itself to studies of high

temperature real gas effects as well as gas dynamic problems at low densities.

(21)

REFERENCES

1. Colin, P. E. ''The Lew Speed Tunnel L-l"~ T.C.E.A. TM 8, October 1960. 2. Ginoux, J.J. : '''rhe T.CoE.A. Continuous Supersonic Wind Tunnel S-l~'

T.C.E.A. TM 7~ October 1960.

3. Chauvin, J.: '''rurbomachinery Laboratory", T.C.E.A. TM 9, November 1960.

4. Fulchignomi~ G. et Hagoulon, J.P.: "Calculs et Installation dlune petite Soufflerie Hypersonique Intermittentel', T.G.E.A. Student Project Report, July 1959.

5. Jensen, J. T.: uPreliminary Design of a Supersonic-Hypersonic Blow

Down Tunnel with an Experimental Analysis of a Heat ExchangerU, T.C.E.A. Student Project, July 1960.

6. Denis, F.: '''rhe Design of a Shock Tube", T.C.E.A. Student Project, July 1959.

7. Benott, A.: "Tube de Choc - Méthodes de Mesure de Températures et de Flux Thermiques, Mise au Point de thermomètres, Etalonnage Préliminaire du Tube de Choc"~ T.C.E.A. Student Project, June 1961.

8. Krt1ckel, H.: "Design of Piezoelectric pressure Transducers and their Application in the T.C.E.A. Shock Tube", T.G.E.A. Student Project, June 1961.

9. Fraser, H. R.: uA Renaissance for the Hydraulic Analogy in the Pedagogical .

(22)

(23)

m

₁

L3~

WT.ld

Electronics

l

Iaboratory

I

Hl

r

J

r---'

I

.

I

a

-

n

J

H .•• 5.

u--Low Speed Wind Tunnels Supersonic Wind Tunnels Hypersonic Wind Tunnels Turbomachinery

High Pressure Air Supply Water Table

Shock Tube

Fig. I EXPERIMENTAL FACILITIES AT T.C.E.A.

L1

J

R2 I Cl R3 L4 RI

~ ~rn~~

LI. L2. L3. L4. SI. 52.53. Hl. H2. Cl. RI.R2.R3. H.P.A.S. W.T. S.T. Access road_

(24)

(25)

I

+

-

-r

"

---,ln' 1 I I :11:: I I 1111 I b-~

i

lWr-=~ 8 ~--rJ ~=3 t::j

J

I. \ t=:l I r I I I I I I I I 1 t-I : I I I I I I , r I I I I I \

1

f-I \ i I I I I I I -I t--J : \ i I I I J I I I r-J i \ : I I I 1 r-1 1 \ i ~ L~ I : I I ~ : i ~l I I

i

~

.

r

1 ___________

t

~~~~

..

~

.

~.Jt

._ - - _. ~ . .

~

-...I ...I UJ Z Z :::::I

....

~ ~ :; z Cl: ...I 0..

(26)

(27)

UJ Z

Z

:::>

(28)

(29)

...

liJ Z Z ;:) ~ Cl Z ~ C liJ

~

9

(30)

(31)

;::) ~

o

z ~ u z o lil 0:: LIJ Q.. ;::) lil

(32)

(33)

UJ Z Z => ~

o

z

~ u

z

o til 0:: UJ

a..

=> til Z

~

~ al

(34)

(35)

t

Blower

Storage heater

Test sect ion 12 cm x 12 cm

1---~

Scale 1 m

(36)

(37)

~I

..:. :I: -' loJ Z Z :;) E ~ u 0 ~

®

ft. ) ( z i

5

~ ~

®

ai z > ~ c: .!! a:: 0

8

loJ Ü Q.

®

>-41 ïL: :I: 111 ;% iii ~ ~ z 0 ;:::: < >-loJ -' loJ ~ ~ loJ > ,g co dl ii:

(38)

(39)

Z Z ::>

....

o

UJ UJ Q. CJl ~ o ....I

(40)

(41)

(42)

(43)

z ~ cJl ~ cJl UJ ~

a::

o ~ o

a::

o UJ UJ Q. cJl en Ó u..

(44)

(45)

z

(/)

o

....

(46)

(47)

-(!) Z ~ a::: a::: c:(w ~t/) t/)::::> wu.. :I:!= ~o o ~U >-Z ( ! ) O Ot/) -Ja::: c:(w Za. c:(::::> Ut/) -J ::::> c:(

~

>-:I:

.-

_u..

(48)

(49)

«

a::

o

al

«

....J (/) U Z o a:: t-U UJ ....J UJ

(50)

(51)

Aerodynamics

Robert H. Korkegi. This note provides a description of

all the existing experimental facili-ties at TCEA, together with a brief

statement of plans for the immediate future.

The facilities include several low-speed and supersonic wind tunnels, a transonic test section, hypersonic

wind tunnels (now being instalied),

turbomachinery, a small shock tube,

TCEA TM 11

Training Center for Experimental

Aerodynamics

statement of plans for the immediate future.

The facilities include several

low-speed and supersonic wind tunnels, a transonic test section, hypersonic

wind tunnels (now being instalied),

1. R.H. Korkegi

II. TCEA TM 11

1. R.H. Korkegi

II. TCEA TM 11

Aerodynamics

Robert H. Korkegi.

This note 'provides a description of

statement of plans for the immediate

future.

low-speed and supersonic wind tunnels, a

transonic test section, hypersonic ,;]ind tunnels (now being installed) ,

TCEA TM 11

Training Center for Experimental

Aerodynamics

all the existing experimental

facili-ties at TCEA, together with a brief statement of plans for the immediate future.

low-speed and supersonic wind tunnels, a transonic test section, hypersonic

wind tunnels (now being installed),

1. R.H. KorKegi

II. TCEA TIi 11

I. R.H. Korkegi

(52)

TCEA TM 11

a water table, and a well-equipped electronics laboratory. As the activities of T.C.E.A. are primarily academic, and

there are at present no facilities in which real gas

phenomena can be studied, it is intended that new equipment should comprise some high-temperature,

low-density devices of modest size.

Copies available at TCEA, Rhode-St-Genèse, Belgium Return this card to TCEA-Library if you require a copy.

TCEA TM 11

a water tab1e, and a we11-equipped electronics laboratory. As the activities of T.C.E.A. are primarily academie, and

there are at present no faci1ities in which real gas

Copies available at TCEA, Rhode-St-Genèse, Belgium

Return this card to TCEA-Library if you require a copy.

TCEA TM 11

a water table, and a well-equipped electronics laboratory.

As the activities of T.C.E.A. are primad[y academic, and

there are at present no facilities in which real gas

10w-density devices of modest size.

Copies avai1ab1e at TCEA, Rhode-St-Genèse, Belgium. Return this card to TCEA-Library i f you requi~e a copy.

TCEA TM 11

a water table, and a well-equipped electronics laboratory.

As the activities of T.C.E.A. are primari1y academie, and

there are at present no faci1ities in which real gas phenomena can be studied, it is intended that new equipment should copprise some high-temperature,

Copies availiable at TCEA, Rhode~St-Genèse, Belgium

(53)

Expérimentale

INSTALLATIONS O'ESSAIS AU C.F.A.E.

Robert H. Korkegi. Cette note donne une description de

tout es les insta11ations d'essais du

CFAE, ainsi que quelques commentaires

concernant les projets pour un avenir rapproché.

Les insta1lations comprennent plusieurs souffleries à faible vitesse et super-soniques, une section d'essai transo-nique, des souffleries hypersoniques

(en voie de montage), des turbomachine~

TCEA TM 11

Centre de Formation en Aérodynamique Expérimentale

toutes les insta1lations d'essais du

CFAE, ainst que quelques commentaires

concernant les projets pour un avenir

rapproché.

Les installations comprennent plusieurs

souffleriès à faible vitesse et super-soniques, une section d'essai transo-nique, des souffleries hypersoniques

(en voie de montage), des turbomachines

1. R.H. Korkegi

II. TCEA TM 11

r. R.H. Korkegi

Ir. TCEA TM 11

Expérimenta1e

tout es les insta1lations d'essais du

Les insta1lations comprennent plusieurs souffleries à faible vitesse et super-soniques, une section d'essai transo-nique, des souffleries hypersoniques

(~n voie de montage), des turbomachines

TeL'. TH 11

Centre de Formation en Aérodynamique Expérimentale

Robert H. Korkegi Cette note donne une description de toutes les installations d'essais du

Les installations comprennent plusieurs souffleries à faible vitesse et super-soniques, une section d'essai transo-nique, des souffleries hypersoniques

(en voie de montage), des turbomachines

1. R.H. Korkegi

Ir. TCEA TM 11

1. R.H. Korkegi

(54)

rCEA TM 11

un petit tube à choc, une table à eau, et un laboratoire d'électronique bien équipé.

Les activités du CFAE étant principalement didactiques, son intérêt se porte également sur l'étude de phénomènes dits de gaz réels. Le Centre ne possède actuel1ement aucune instal1ation permettant de telles études, mais il est envisagé de développer des dispositifs d'essais de

dimensions modestes à hautes températures et faibles

densités.

Copies disponibles au CFAE, Rhode-St-Genèse, Belgique.

Renvoyez la fiche au CFAE-Bibliothèque si vous désirez ce rapport.

TCEA TM 11

un petit tube à choc, une table à eau, et un laboratoire d'électronique bien équipé.

Les activités du CFAE étant principalement didactiques,

son intér~t se porte également sur l'étude de phénomènes

dits de gaz réels. Le Centre ne possède actuel1ement

aucune installation permettant de telles êtudes, mais il est envisagé de développer des dispositifs d'essais de .

densités.

Copies disponibles au CFAE, Rhode-St-Genèse, Belgique.

Renvoyez la fiche au CFAE-Bibliothèque si vous désirez

ce rapport.

rCEA TM 11

un petit tube à choc, une table à eau, et un 1aboratoire . d'électronique bien êquipé.

Les activités du CFAE étant principalement didactiques, son intérêt se porte également sur l'étude de phénomènes

dits de gaz réels. Le Centre ne possède actuellement

aucune insta11ation permettant de tel les études, mais i1 est envisagé de développer des dispositifs d'essais de

densités.

Copies disponibles au CFAE, Rhode-St-Genèse, Belgique. Renvoyez la fiche au CFAE-Bibliothèque si vous désirez ce rapport.

rCEA TM 11

un petit tube l cboc, une table à eau, et un laboratoire d'électronique bien équipé.

Les activités du CFAE étant principalement didactiques,

son intérêt se porte également sur l'étude de phénomènes

dits de gaz réels. Le Centre ne possède actuellement

aucune instal1ation permettant de telles études, mais il est envisagé de développer des dispositifs d'essais de

densités.

Copies disponibles au CFAE, Rhode-St-Genèse, Be1gique.

Renvoyez la fiche au CFAE-Bibliothèque si vous désirez