ANNUAL PROGRESS REPORT
1978
1978
TECHNISCHE HOGESCHO 1
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\919FOREWORD
The Institute's balance of research and direct teaching, and that of more basic research and contractual research, is unusual compared with that of most University departments. In particular, our research is based to a considerable extent on experimental work in major installations. Possession of these facilities and the timely incorporation of new innovative research techniques have provided unique opportunities to undertake leading research on a significant scale. These facilities and laboratories are described in a dedicated section of this report, pages 16-32. The dependence on such major installations also creates unusual and costly problems of upkeep not generally encountered in university laboratories. Specific financial support is mandatory to cover these special costs in order to maintain the capability that represents in a major way the co re of the Institute's work.
There has been a growing conc~rn within the country, especially over the past few years, about de-industrialization of the economy and the low level of Canadian R & D as a contributing factor to this decline. Against this background it is worthy of note that our contact with the aeronautical and space industry remains a close one and that the interaction is active and fruitful in both directions. We are looking forward to continuing this collaboration and strengthening it further. It is a matter of some pride that the Institute has been involved in substantial technology transfer to Canadian industry in a number of new areas during the past year.
Technical spin-off of Institute R & D has come to direct fruition in collaboration with Sciex Limited, a Canadian company which has successfully marketed an advanced trace gas analysis device, see page 59. These devices are currently finding wide-ranging applications from environmental monitoring to new methods of medical diagnosis. Technology originally developed for hypervelocity research at UTIAS is now the subject of study by the 3M Company of Canada Limited for commercial application. A research team from this
company, under the direction of Dr. N. Salansky, is stationed at the Institute to study the production of new materials using the explosive-driven implosion facilities that were developed in earl ier Institute studies on the formation of diamonds from graphite, see page 42. A third instance is in the field of fusion technology, an area of sustained interest at the Institute as indicated in previous annual reports, as well as the present one, see page 38. The consulting firm of DSMA ATCON Limited has posted an engineer full-time at the Institute to participate in and contribute to our research program in this area, while becoming familiar with this new technology in preparation for future work with the company.
Professor H. S. Ribner retired from his full-time position during this year, but is staying actively on the staff on a part-time basis, and we welcome Prof. W. G. Richarz who recently joined us as a new staff member, with interests in the aero-acoustic field.
J. H. de Leeuw, Director.
Personnel t~jor lnstallations Institute Laboratories Progress Reports TABLE OF CONTENTS Page 4 16 25 Aeroacoustics 33
Air Cushion Technology 36
Energy Technology 38
Flight Transportation 40
Gasdynamics and Shock-\Jave Phenomena 42 lndustrial and Architectural Aerodynamics 44 Laser Excitation and Diagnostic Applications 45
Psychoacoustic Research 47
Rarefied Gas and Plasma Dynamics 48
Sonic Boom and Thunder 49
Space Dynamics and Control 51
Space Simulation and Molecular Beams 53 Structural t1echanics and t1ateriai s Science 54
Subsonic Aerodynamics 57
Trace Gas Analysis 59
Upper Atmospheric and Flight Research 62 UïlAS Publications
STAFF OF THE INSTITUTE FOR AEROSPACE STUDIES
PROFESSOR AND DIRECTOR OF THE INSTITUTE
J. H. de Leeuw, Dipl. Eng. (Delft), 11.S. in A.E. (Georgia Tech.), Ph.D., F.R.C.S., F.C.A.S.I., F.A.P.S.
PROFESSOR AND ASSOCIATE DIRECTOR
J. B. French, t1.Sc. (Birmingham), B.A.Sc., Ph.D., F.C.A.S.I., F.R.S.A. ASSOCIATE PROFESSOR AND ASSOCIATE DIRECTOR
P. C. Stangeby, Dipl.-Sci., D.Phil. (Oxon), B.Sc., M.Sc. PROFESSORS
B. Etkin, D.Eng. (Carleton), B.A.Sc., ~1.A.Sc., F.R.S.C., F.C.A.S.I.
F.A.I.A.A., Dean of the Faculty of Applied Science and Engineering I. I. Glass, B.A.Sc., t~.A.Sc., Ph.D., F.A.P.S., F.A.A.A.S., F.C.A.S.I.,
F.A.I.A.A., F.R.S.C.
P. C. Hughes, B.A.Sc., t1.A.Sc., Ph.[)., F.C.A.S. I. R. 11. t1easures, B.Sc., A.R.C.S., D.I.C., Ph.D. (Lond.)
H. S. Ribner, B.S. (Cal. Tech.), r1.S., Ph.D. (Hash. (St. Louis)), F.R.S.C., F.C.A.S.I., F.A.I.A.A., F.I\.P.S., F.A.S.A.
R. C. Tennyson, B.A.Sc., ItA.Sc., Ph.D., F.C.A.S.1. VISITIIJG PROFESSOR
K. Takayallla, Dr.Eng. (Tohoku) ASSOCIATE PROFESSORS
J. D. DeLaurier, B.S. (Illin.), ltS., Ph.D. (Stan.) G. vJ. Johnston, B.A.Sc., ttA.Sc., Ph.D., F.C.A.S. I. L. D. Reid, B.A.Sc., ~1.A.Sc., Ph.D.
P. A. Sullivan, B.E., r1.E. (rl.S.H.), D.I.C., Ph.D. (Lond.) ASSISTANT PROFESSORS
A. A. Haasz, B.A.Sc., 11.A.Sc., Ph.D.
J. S. Hansen, B.A.Sc., t1.A.Sc., Ph.D. nJaterloo) W. G. Ricllarz, B.A.Sc., t~.A.Sc., Ph.D.
ADJUNCT PROFESSOR
F. Cicci, B.A.Sc., ~1.A.Sc., Ph.[).
SENIOR RESEARCH ASSOCIATE
rl. f~. Reid, B.Sc., Ph.D. (St. Andrewis), C.Chem., M.R.I.C.
RESEARCH ASSOCIATES
S. C. Garg, B. Tech. (Kanpur) , t1.A.Sc., Ph.D.
J. P. Sislian, t~.Sc. (Yerevan), Cand. Phys. & t~ath. Sci. (l1osco\lJ) , Ph.D.
RESEARCH STAFF
G. Ben-Dor, B.Sc., f·1.Sc. (Ben-Gurion), Ph.D. W. E. R. Davies, B.Sc. (Ottawa)
W. O. Graf, B.Sc., M.Sc.(Eng.) (Pretoria) A. K. Kudian, G.Sc., t1.Sc., Ph.D.
I. t1urra, Dipl.lng. (Belgrade), t1.A.Sc.
C. C. Poon, B.E., B.Sc. (Tas. U.), /1.S. (Syr. U.), Ph.D. (Cal.) S. Rail'1ondo, B.A.Sc., t1.A.Sc.
P. L. Sears, r·1.A., Ph.D. (Cantab)
W. T. Shmayda, B.Sc. (Queenls), r,1.A.Sc., Ph.D.
Y. D. Tsay, B.S. (Taipei), M.S. (Hsinchu), Ph.D. (Rhode I.) I. Youle, B.Sc. (Dal.), M.A.Sc.
CONSULTANT
W. Czerwinski, Dipl.-Ing. (Warsaw), F.C.A.S.I. LIBRARIAN
r1rs. Asta luik, B.A. (Estonia), B.l.S., r1.l.S. (Toronto) RÏ!,'SEARCH ASSISTANTS
M. S. Abu Khalaf J. R. J. de lafontaine
D. Adamko J. [Jenes
S. Ando D. Dignam
r1. Arnfield ~1. Drewell
K. l. AslwlOrth A. Dupuis
tI. Ball B. C. Eatock
R. P. Baronet J. D. Fairgrieve
C. G. Barringer A. Ga k\~aya
D. S. Breitrlan P. T. Gartenburg
C. J. Bryant t1. J. Gil i berto
W. l. Buchanan D. Golla J. l. Campbe 11 P. R. Hartl'lann P. Cardinal E. G. Hartwell J. A. Catalano l. P. H'êbert V. Chatoorgoon G. R. Heppler P. Chodas t·1. J. Hinchey
I. Y.-P. Chung P. K. Hodes
t1. A. Daoud O. Holst-Jensen
T. E. [Ja rc i e R. P. Holzer
D. F. Davidson D. Hui
RESEARCH ASSISTAflITS (ContinuedJ t~. Jankovic J. G. Kavanagh B. Kroeker H. S. Kwong B. A. Lay J. H. Lever 13. J. Lewis C. Lombardi G. t~abson D. J. f~acDona 1 d G. E. rlacDonald A. 13. f~arkov W. D. fkKinney I. R. t1cLean rL J. t1c1 J ei 11 ~J.
u.
t~orison S. r~acson A. P. rJanyaro A. i~iedzwiecki U. J. fJoble [). Nussbaur.1 K. Ogirnoto P. Palumbo J. G. Parravano D. H. Pepper S. Podleski J. Potj ewyd SUPPORT STAFFc.
Basdeo J. L. llradbury J.w.
E. Brandonw.
Dillon D. lJouglas R. Eisen [). Finlay t1. Fitzgera 1 d H. Kleinberg J. Leffers 6 P. Pulinec D. Ribner D. Roy T. Saito D. t1. Schenck L.w.
S i 9 u rd s 0 n D. E. Simmons G. B. Sincarsin A. A. Smailys E. tL Solol'/ka P. Spedaler H. Teichman C. Tessier W. G. Timbers B. T. Uffen A. H. von Flotow S. Vukicevic N. N. Wahba G. ~Ja ters A. Weiss G. S. West-Vukovich G. E. Hharrarn C. I. \tJi11is P. L. Wizinowich R. Hong S. S. K. ~'Jong J. H. tkCormack E. t1i 11 s A. t10rte A. Perrin L. Quintero H. Ryan G. Sachade H. Schur:lacher G. Singh J. TonigoldTile Gordon 11. Patterson Lecture is given annually in honour of the Founder of tile Institute by a distinguished graduate of the Institute. This yearls Lecturer, Dr. D. G. Gould, Principal Research Officer in the Flight Research Laboratory of the I~ational I\eronautical Establishment, received his Ph.D. under the supervision of Prof. I. I. Glass in 1952. Dr. flould spoke on "A Consideration of Some Fl ight ~1echanics Problems from the Viewpoint of Encouraging Research on Pilot Control Behaviour". In his lecture Dr. Gould described hovi an improved understanding of the nature of pilot control behaviour I'Jill enable more definitive engineering studies of the dynamic response of aircraft to ue made, and presented supporting results from recent piloted simulation studies of V/STOL aircraft performed at the Flight Research Laboratory of the fjAE.
On the occasion of the Lecture, wllich \tas held on October 13, the G. 11. Patterson Student I\ward for outstandi ng schol arshi p was presented to Dr. G. Ben-Dor. Dr. Ben-Dor received his doctorate this fall under the supervision of Prof. I. I. Glass on the topic of "Region and Transitions of tJonstationary Ob-1 ique Shock-~Jave Diffractions in Perfect and Imperfect Gases". Shown above from left to rigilt: Drs. G. 11. Patterson, D. G. Gould, G. Ben-Dor and J. H. de Leeuw.
Dr. J. B. French obtained his B.A.Sc. in Chemical Engineering, University of Toronto, M.A.Sc. in Thermodynamics at Birmingham, England, and Ph.D. in Plas-madynamics at UTIAS, where he joined the staff in 1961. His general fields of interest include gas dynamic mole-cular beams, space simulation, trace gas analysis instrumentation development,
Professor J. H. de Leeuw obtained his Engineering Diploma in Aeronautical Engineering at the Delft Technical University in Holland. He obtained his M.S. degree in Aeronautical Engineering at the Georgia Institute of Technology and his Ph.D. in Aerophysics at the Institute for Aerospace Studies of the University of Toronto. He joined the staff of UTIAS in 1958 and is now
Director of the Institute. His original interest in shock tubes and their use in MHD research shifted subsequently to largely experimental work in low density gas and plasma flows with a special em-phasis on the development of new measuring techniques. Adaptations of these labora-tory techniques led to the construction of special rocket instruments for the measure-ment of the properties of the upper atmos-phere. More recently his interests have included flow problems associated with fusion technology. Professor de Leeuw is a member of the NRC Advisory Committee on Fusion Research, he is a Fellow of the Canadian Aeronautics and Space Institute and a Fellow of the American Physical Society.
and many applications of the latter in environmental, military, medical and other areas. His projects included ion source development with Prof. A. O. Nier of Minnesota for the highly successful Project Viking Martian up per atmospheric mass spectrometer. His research has led to major advances in atmospheric pressure chemical ionization mass spectroscopy. Patents which make APCI/MS practical as a research and analytic tool (held jointly with N. M. Reid, J. A. Buckley) have been developed in Canada into a commercial instrument. Recently, Dr. French has been appointed to hold a watching Brief for NRC on Satellite Solar Power systems. He is a Fellow of the Canadian Aeronautics and Space
Institute, a Fellow of the Royal Society of Arts, and a member of the AIAA and the AlP.
Dr. B. Etkin obtained his B.A.Sc. degree in Engineering Physics at the University of Toronto and an M.A.Sc.
in Aeronautical Engineering. He has
been on the staff of the Engineering Faculty since 1942. He served as Chair-man of the Division of Engineering Science from 1967-1972 and has been Dean of the Faculty since 1973. His research interests have included air-craft structures, wing theory, shock waves, stability and control of aircraft,
satellites and re~entry vehicles and
aerosonics. His two books on "Dynamics of Fl ight" have been widely used in English, Russian and German editions. He has served for many years as a con-sultant to U.S. and Canadian industry and government and spent considerable time in the aircraft industry during and af ter World War 11. His current research
interests include the effects of atmos-pheric turbulence on flight vehicles, lighter-than-air aircraft, applications of air curtains, and aerodynamic means of sorting fine particles. He is a Fellow of the Royal Society of Canada,
of the CASI, and of the AIAA. He
recei ved the rkCurdy Award in 1969, an honorary D.Eng. from Carleton University in 1971, and the Mechanics and Control of Flight Award of the AIAA in 1975.
Dr. P. C. Stangeby obtained his Bach-elor and Master degrees in Mathematics and Physics at the University of Toronto, and his Doctorate in Engineering Science
(Plasmas) at Oxford University, joining the Institute staff in 1972. His general field of interest is applied physics, and in particular, energy technology. Dr. Stangeby's current research emphasis is
in the fusion energy area 'including study
of the Gas Target ~eutron Generator
con-cept for fusion engineering research and plasma-surface interaction research using the Space Simulator. Other energy research interests include hydrocarbon fuels (oil sand and coal), plasma device technology and magnetohydrodynamic power generation. Dr. Stangeby is a menber of the Canadian Association of Physicists, the (UK) Insti-tute of Physics, and the American InstiInsti-tute of Aeronautics and Astronautics.
Professor P. C. Hughes obtained his Ph.D. from the University of Toronto (1966) in Aerospace Engineering Science. t10st of his research has been related to space vehicle dynamics and control, including significant contributions to the dynamical model-1 ing of the Alouette/lSIS and Hermes satellites and of the NASA Space Shuttle manipulator arm. Current interests include the application of modern control theory to this class of applications, and the dynamics and control of large space structures. Professor Hughes is a Fellow of the Canadian Aeronautics and Space
Institute, and reviews regularly for the U.S. aerospace journals.
10
Professor I. I. Glass obtained his Elachelor and t1aster degrees (Engineering Physics-Aeronautical Engineering) and Doctorate (Aerophysics) at the University of Toronto in 1950, when he joined UTIAS. His fields of study have centred on gas-dynamics and shock-wave phenonena. He is currentlv interested in shock structure
and stab~lity, shock-tube sidewall and
flat-plate la~inar boundary layers in ionizing argon and krypton; implosion dynamics with a view to fusion diagnostics and new materials; effects of sonic boom on structures and shock transitions in rl-waves; condensation shock waves, geo-thermal energy and turbulent combustion. Professor Glass is a Fellow of the Royal Society of Canada, the American Physical Society, the Anerican Institute of Aero-nautics and AstroAero-nautics and other Insti-tutions.
Dr. H. S. Ribner obtained his B.S.
Dr. Raymond Measures obtained his Bachelor and Doctorate degrees in Honours Physics at Imperial College of Science and Technology, London University, England. He has worked in the area of applied physics since he joined the staff of thp. Institute in 1964. His early work involved the measurement of atomie collision cross sections by laser interferometric studies of shock waves and the devel-opment of a new approach at local plasma diagnostics using laser selective excitation spectroscopy. Dr. Measures was recently promoted to the rank of Professor. His current interests centre on several laser projects ranging from the developrnent of a new kind of Trace Element Micro-probe to the study of efficient ionization using laser resonance pumping.
from Caltech and his M.S. and Ph.D. (1939) from \'Jashington University (St. Louis), al~ in physics. Af ter a short period in gravity meter development, he spent eight years at the NACA (predeces-sor of NASA) Langley Laboratory and five years at the Lewis Laboratory, variously as aerodynamicist and section head (Stability and Control Section, Langley, Boundary Layer Sections, Lewis). He joined the Institute staff in 1955, was a Visiting Professor at University of Southampton in 1960-61, and a Staff Scientist at NASA Langley in 1975-76. His research interests have covered, somewhat chronologically, X-rays, cosmie rays, gravimetry, aerodynamics, aero-acoustics, sonic boom, and the acoustics of thunder. Prof. Ribner is a Fellow of the Royal Society of Canada, the Canadian Aeronautics and Space Institute (CASI) and several American societies. He was the CASI Turnbull Lecturer in 1968, Chairman of the ICAO Sonic Boom Panel
in 1970-71, and received the AIAA Aeroacoustics Award in 1976.
Dr. DeLaurier obtained his Bachelor
Prof. R. C. Tennyson obtained his
B.A.Sc. at the University of Toronto
and his graduate degrees (M.A.Sc., Ph.D.) at the Institute for Aerospace Studies. Af ter joining the Institute staff in 1965, he continued to work in the Structura1 Mechanics area with special interest in shell buck1ing prob1ems. During these intervening years, his interests have expanded to
inc1ude stress waves in solids, com-posite materials, biomechanics and space simu1ation studies. Dr. Tennyson is a member of the Nationa1 Research Counci1 of Canada Associate Committee on Aerospace Structures and Materials, the American Institute of Aeronautics and Astronautics and a Fe11o\'J of the Canadian Aeronautics and Space Institute.
degree fro~ the University of I11inois, af ter \'Jhich he worked as an aerodynar.1-icist at IkDonnell Aircraft. Subse-quent1y, he \'Jent to Stanford University where he received a Master and Ph.D. degree (1970). Af ter a year at the von Karman Institute for F1uid Dynamics, Dr. DeLaurier returned to industry, first, as a balloon analyst at She1dah1 Inc., and next, as a research engineer at Batte11e r1emoria1 Institute. Upon joining the staff at UTIAS in late 1974, Dr. DeLaurier has continued his work on Lighter-than-Air Techno1ogy, where he has deve10ped programs for predicting the stabi1ity and control of modern airships, and their response to atmos-pheric turbu1ence. Other research interests inc1ude unsteadv subsonic aerodynamics and subsonic~ separated f10ws invo1ving bound vortices. Dr. DeLaurier is a member of the Interna-tional Astronautica1 Federation's subcomr.1ittee of Lighter-than-Air Techno1ogy, and is a revie\'Jer for App1ied Mechanics Reviews.
Dr. L. D. Reid earned his B.A.Sc., M.A.Sc. and Ph.D. degrees in Aerospace Engineering at the University of
Toronto. He first joined the staff of the Institute as a Special Lecturer in 1965 and is presently an Associate Professor. His research interests lie in the general areas of aircraft sta-bility and control and piloted aircraft performance. At the present time Dr. Reid is investigating the response of aircraft to wind shear and low altitude turbulence during the landing approach. This work involves wind tunnel measure-ments, piloted flight simulators and computer simulations. Ot her current research interests include the on-line computer control of wind tunnel opera-tions, the development of Laser Doppler Anernometry and the study of the per-formance of automobile drivers. Dr. Reid is an Associate Fellow of the
Canadian Aeronautics and Space Institute and of the American Institute of Aero-nautics and AstroAero-nautics.
Professor G. W. Johnston received his Ph.D. from the University of Toronto, Institute of Aerophysics (1953). He spent 10 years with the de Havilland Aircraft Co. of Canada being responsible for a number of advanced STOL research and development projects. He joined the Research Laboratories of the United Tech-nologies Corp., East Hartford, Connecticut, in 1967 as Aerodynamic Consultant to their Fluid Dynamics Department. Activities here included the creation and development of a basic aeroacoustics research group and development of the anechoic wind tunnel facility. He joined the Institute staff in 1970 specializing in aeroacoustic research. Current research interests include the development and propagation of sound by aerodynamic bodies. Subjective "annoyance" research is also of continuing interest. Dr. Johnston is a Fellow of the Canadian Aeronautics and Space Institute.
Dr. A. A. Haasz obtained his B.A.Sc. in Engineering Science and his M.A.Sc. and Ph.D. degrees in Aerospace Science and Engineering at the University of Toronto. His fields of study included electron impact excitation cross
sec-tion measurements for at~ospheric
species, and thermospheric composition/ temperature measurements with electron beam fluorescence probes. Af ter joining the Institute staff in 1972, his research interests expanded to inc1ude studies of
Gas Target ~eutron Generators (related
to fusion energy techno1ogy), industrial/ architectura1 aerodynamics (viz studies of air-curtain jets used for protection against precipitation and a1so for con-finement of environmenta11y hazardous chemica1s and particulates), and sub-jective "annoyance" studies of aircraft and traffic noi se. Recent research efforts are directed towards Materials damage studies for fusion reactor applications. Or. Haasz is a member of CAP, CASI, APS and AIAA; he is also a registered professional engineer.
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Dr. P. A. Sullivan obtained his Bachelorls and Masterls degrees in Mechanica1 Engineering at the Univer-sity of Ne\'1 South Wales, Austral ia, and then travelled to England to work for his Doctorate in Aeronautics at the Imperia1 College of Science and Technology, London. Af ter a post-doctoral year at Princeton University, he joined UTIAS in the fall of 1965, where he pursued his research interests in hypersonic aerodynamics and boundary layers. In response to declining in-terest in this area in Canada in the
early 19701
s, and to renewed Canadian interest in air cushion vehicles, he developed a research program in the latter area. With the aid of generous funding from the National Research Council of Canada and the Transporta-tion Development Agency this program is now well established. Dr. Sullivan is an Associate Fellow of the Canadian Aeronautics and Space Institute, and of the American Institute for Aero-nautics and AstroAero-nautics. He is a licensed professional engineer and has active consultancies in air cushion
Dr. W. G. Richarz obtained his B.A.Sc., M.A.Sc. and Ph.D. degrees in Aerospace Science and Engineering at the University of Toronto before joining the Institute Staff in August, 1978. His fields of study included eombustion noise, performance of acoustie barriers, and jet noise. Current research een tres on theoretical and experi-mental aeroacoustics with emphasis on jet noise diagnostics and reduction. Other areas of interest are turbulence, fluid flow measurements, sueh as laser Doppler velocimetry, and data analysis techniques.
15
Dr. Ilansen obtained his B.A.Sc., M.A.Sc. and Ph.D. degrees in the Division of Solid Mechanics of the Department of Civil Engineering at the University of VJaterloo. He joined the Institute staff in 1975 af ter working at the Technical University of Denmark and at University College, London, England as a NATO Postdoctorate Fellow. Dr. lIansen ' s current research emphasis is primarily in solid mechanics whieh includes programs in the theory of elastic stability, fracture mechanics, erashworthiness of aireraft structures, influence of the spa ce environment on composite materials and the finite element methode
MAJOR INSTALLATIONS
AIR CUSHION VEHICLE TEST TRACK
This 45m diameter enclosed circular test track constitutes a unique facility for experimentation on air cushion vehicles under controlled conditions. The vehicle under test, up to 5m long and 1000 Kg in weight, is tethered to a central post. Instrumentation data on vehicle ~otions are passed along the tether and through a slip ring to an HP 2100A computer. Moveable track panels permit studies of vehi-cle stability for ramp traversal.
This facility was designed for the investigation of dissociating and ionizing-gas flows encountered during hypervelocity flight. It consists of a l5-cm-dia combustion chamber (2H2 + O2 + 7He), a recoil section, and a transition section (upper photo) to a 10 cm x 18 cm x 16 m channel, test
section, recoil section and dump tank (lower photo). The major measuring instrument is a Mach-Zehnder inter-ferometer with a 23-cm-dia field of view. A'Q-switched giant-pulse ruby (or neodymium) laser light souree with a Pockell cell and frequency doubler provide dual-wavelength inter-ferograms. From these it is possible to measure point-by-point electron number density and total density in the flow field. Pre-scribed stainless steel diaphragms are used up to com-bustion pressures of 400 atm. Cylin-drical deflagratipn is initiated by an impulsively-heated tungsten wire. Channel pressures ~o ~ 10-5 torr with
a leak rate of 10- torr/min are possible. Shock Mach numbers Ms - 25 in argon at Po - 0.3 torr can be produced with degree.s of ionization
x - 50~L Piezo-pressure gauges,
thin-film heat gauges and other instrumenta-tion are also utilized.
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HYPERVELOCITY
SHOCK TUBE
~
LOW DENSITY WIND TUNNEL
The Institute's Low Density Wind Tunnel, LDWT, was constructed for studies of rarefied gasdynamics and to simulate the near space environment. The LDWT consists of nine vacuum booster pumps capable of 18,000 l/S pumping speed at 10-2 torr, backed by Roots Blowers and mecllanical pumps. Currently, the LDWT is finding
application outside the traditional aerospace field, in fusion energy studies on a gas target neutron generator
concept. Such studies are only possible with large gas pumping facilities, such as the LDWT, which are generally unique to aerospace laboratories.
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o
PLASMA TUNNEL
The Plasma Tunnel is a low density flow facility which can be operated in different pumping modes. It can be
operated at background flow pressures up to about 10 Pascal (1 Pascal = 1.3 micron of Hg) at volume flow rates
of several 1000 liter/sec. Alternatively, it can provide working pressures near its blank-off pressure of about 5 x 10-3p at effective flow rates of 500 ~/sec. Plasma flows can be produced by an RF arc source operating near atmospheric pressure and temperatures of 5000K or by an ion thruster providing high speed-ratio plasma flows for
low mass flow applications. The test section, with a diameter of 2m and a volume of 15m3, is equipped with a
traversing mechanism, extensive pressure instrumentation, and an electron beam fluorescence probe. It is a con-venient test chamber for a variety of tests at intermediate vacuum levels.
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SONIC BOOM SIMULATORS
Two major facilities exist at UTIAS forinvestigat-ing the effects of sonic boom on humans, animals, and structures. The booth (upper left) driven by
12 loudspeakers, yields accurate vJaveform
sir.1ula-tion; it is most useful for psychoacoustic studies.
The horn (right, top and bottom) is a 3m x 3m x 26m
horizontal pyramid, driven by either a shock-tube or special compressed-air valve; its very powerful
booms are useful for a variety of problems,
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SPACE SIMULATION AND MOLECULAR BEAMS FACILITY
The facilities consist of a high speed gasdynamic molecular beam system, with recently developed intense
mono-energetic atomic hydrogen and atomic oxygen sources for simulating upper planetary orbital flight, for basic studies of reactive gas-surface interactions, for development of spacecraft instrumentation or for simulation of atmospheric surface effects in orbit on advanced engineering materials, such as composites, etc. A 9 ft
diameter ultra clean, ultra high vacuum thermal vacuum space simulation chamber is available, and molecular beams of up to several centimeters in diameter can be introduced. Several smaller chambers are available for
specialized studies, and include a variety of mass spectrometer, vacuum, surface deposition and other
instru-mentation. Recently the Space Simulator has been used for plasma-surface interaction studies of interest in fusion energy development.
General view of wind tunnel.
SUBSONIC
The subsonic wind tunnel was originally designed to perform aerodynamic tests on aircraft and aircraft components in a low turbulence test section. As our research emphasis shifted towards an interest in the influence of turbulence on aerodynamic performance a decision was made to recon-figure the test section into one more suited to such work. A recently completed program has converted the facility into a boundary layer wind tunnel capable of a wide range of turbulent flow simulations. The tunnel has a closed circuit and is powered by both a fan in the return duct and by a unique jet grid fed from an external blower. Control over the flow from this jet grid is used to tailor the ve loc ity prof il e in the 1. 1 m xl. 7m test section.
The wind tunnel laboratory instrumenta-tion includes 4 channels of DISA hot wire anemometry, a TR-48 analog compu~er and a HP 2l00A digital computer. This equipment
is used to set up the flow conditions in the tunnel and to take measurements and analyze data. Sharing the computers is a general purpose manned simulation facility used for a variety of man/machine system eval uations.
WIND TUNNEL
General purpose manned simulation facility. Analog and digital computers.
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VACUUM SPHERE AND HOT FLOW TEST FACILITY
The vacuum sphere, of volume 1000 m3 , can be pumped down to less than 10-3 atm pressure, and used as a high
mass-flow, blow-down test facility, e.g., as a hypersonic wind tunnel. The vacuum pumping plant, insert, can also operate in a compression mode and in conjunction with an electric gas heater can perform as a hot flow test facility with typical continuously-operating characteristics: 0.5 kg/s, 300°C, 1 atm overpressure.
INSTITUTE LABORATORIES
AEROACOUSTICS LABORATORY
Aeroacoustics is the study of noise associated with airflow and flow devices. UTIAS researches spread over two decades - both experimental and theoretical - have included aeolian tones, the noise from boundary layers, jets, turbofans and combustion, as well as sonic boom and thunder. The UTIAS Aeroacoustics Laboratory aside fr om the Sonic Boom Simulators -centres around the two anechoic chambers pictured above. Both accom~odate
a 3/4" air jet, and the right-hand one r:1ay be traversed by a 3 foot open
jet at up to 225 ft/s. In addition there is a duct flmJ facility (e.g., 8" x 10" x 36 feet) with comparable flmv speeds. For data processing th ere
is a dedicated HP2l00A computer with fast
AID
andDIA
input and output. For auto- and cross-correlations of random signals, FFT, cross-spectral density, signal averaging, etc., th ere is a new DSP360 digital signal processor. Measurer:1ent of jet turbulence is via constant temperature hot-wire jets (2) and the recently developed UTIAS Laser Doppler Syste~.All this is suppler.lented by a variety of condenser microphones, spectrum analyzers, level recorders, oscilloscopes, calibrators, etc.
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IMPLOSION DYNAMICS LABORATORY
A 20-cm dia hemispherical i~plosion chamber is the major piece of equipment. The chamber is machined into a massive steel block, which is closed by a massive steel plate, both fastened by 32 x 3.8 cm dia bolts.
Stoi-chiometric oxygen-hydrogen (up to 60 atm) is detonated at the centre by a short (1 mil dia x 1 mm long)
exploding nickel wire. The detonation wave initiates a hemispherical shell of PETtl at the periphery of the chamber and a powerful implosion follows. As far as we know this is the only laboratory capable of producing stable focussed explosive-driven implosions in a safe reusable facility. It has been used to drive projectiles to hypervelocity, to generate planar shock waves in a 2.54 cm channel at 20,000 mis, and produce diamonds from graphite. Other new materials could well be generated through solid-phase transitions. An image converter camera, a Hilger medium quartz spectroscope with a 6-photocell Strassheim attachment, piezo gauges, and pure iron "witness plates" are utilized for measuring temperatures and pressures as functions of radius and time.
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INSTITUTE COMPUTERS
The Institute has a computer terminal directly linked to the massive digital computers on the main (St. George)
campus. This is accomplished by a general purpose IBM 1130 digital computer which also has a stand-alone
capability and which may be used to drive a Calcom plotter. Other more specialized analog and digital computers are used in specific research programs at the Institute. A modern analog computer (St. George Campus) which can be used as a hybrid computer is available to UTIAS researchers. A full time terminal coordinator 1s available to assist in resolving computational difficulties.
LASER LABORATORY
The Institute's Laser Laboratory currently uses two nitrogen lasers, two laser pumped tunable dye lasers, one flashlamp pumped tunable dye laser and one Q-switched pulsed ruby laser. These lasers are used in a variety of projects and form the backbone of two main facilities: the Laser Ablation and Selective Excitation Spectroscopy (LASES) facility and the Fluoromonitor facility. The LASES facility has recently been shown to be capable of undertaking several experiments ranging from the measurement of atomie radiative lifetimes to the study of collisional coupling. This facility has also served as the work horse of a new approach to trace element analysis. The Fluoromonitor facility presently under development will represent, when completed, a versatile instrument for
evaluating the fluorescent characteristics of a diverse class of target materials.
It will also serve as the prototYr>e of a new class of "on line" quality control
monitors that could have application to industry.
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PRECIPITATION WIND TUNNEL LABORATORY
The UTIAS precipitation wind tunnel has a working test section of about lm x lm cross sectional area and 5m
length, and operates in the 0-3 mis speed range. The precipitation feature of the tunnel consists of a
cylindrical hopper containing the simulation material, which is being traversed automatically at preselected speeds in the x-y directions in a horizontal plane above an opening in the tunnel roof. The precipitation is simulated by glass beads of appropriate sizes and densities to yield the desired terminal velocity ranges. The bead feed system is equipped with control features for varying the bead mass flow rate, which is essential
in order to ensure that the particles introduced into the tunnel travel through the flow field without inter-acting with each other.
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SHELL MECHANICS
SPACE SIMULATOR
". '~
AIRCRAFT CRASH FACILITY
STRUCTURES end MATERlALS
LABORATORY
The major facilities contained in this laboratory include a universal tensionjcompression testing machine (60,000 lbs capacity), a thermal-vacuum space simulator, capab1e of 10-7
torr with in-situ loading, a 13 foot long high pressure gas gun for impact studies, fatigue machines, a belt-wrapper apparatus
and autoclave for manufacturing conposite structures and an
aircraft fuselage (~1/3 scale) drop test facility for investi-gating crash response.
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TRACE GAS ANALYSIS LABORATORY
The laboratory is centred around a highly flexible atmospheric pressure chemical ionization mass spectrometer
system. This has different inlets to be able to accept different samples such as ambient air, gas chromatograph effluents, volatized liquid samples, etc. It is currently capable of detecting many trace organic substances in
air at parts per trillion concentrations instantaneously in real-time. Developmental research is steadily
improving its performance. The facilities also include a variety of developmental vacuum chamber quadrupole
mass spectrometers, ion sources, an electron multiplier test facility, analogue and digital electronic equipment, and a dynamic calibration facility capable of adding kno~Jn trace amounts of organics to air, in the ppm to ppt range. The laboratory is currently engaged in applications research in biomedical, military and environmental areas. A basic program to provide better understanding of the transmission of ions into, through and out of quadrupole mass filters has been initiated as a collaborative project with the Physics Division of NRC, aimed at innovative improvements in this important technology.
AEROACOUST I CS
Principal Investigator: Ph.D. Students:
M.A.Sc. Students:
PROGRESS REPORTS
G. W. Johnston, H. S. Ribner, W. Richarz B. Eatock, D. Noble, K. Ogimoto, W. Richarz, R. Wong
N. Ball, D. Dignam, I. McLean, D. Breitman
JET NOISE DIAGNOSTICS VIA LASER DOPPLER (NRC; AFOSR) Jet noi se di agnosti cs
have been performed by cross-correlating the suspected source terms (e.g., rates of turbulent momentum flux) with the effect they produce. To eliminate the possibility of spurious noise due to hot wire-flow interference, the source terms were measured with a Laser Doppler Velocimeter (af ter a lengthy period of development) and correlated with the far field jet noise (microphone signal). Source distribution over slices of jet inferred therefrom are unex-pectedly somewhat pear-shaped. Spectra predicted from measured cross-spectral densities are compatible with corresponding spectra extracted from far field intensities and with theory. (Elaborated in Ph.D. Thesis.)
JET NOISE SUPPRESSION (NRC; AFOSR) Experimental studies of some unorthodox
concepts for shielding jet noise have been carried out. Only modest attenua-tion of the peak jet noise was found vlith a family of half-round "sugar SCOOp" shields (e.g., 5-6 PNdB when scaled to a full size engine), owing largely to
"edge noise" from jet interference. Another shielding concept involved
extending the effective length of the "sugar ScOOpS" by means of a hot refrac-tive layer (~rray of flames). Marginal increases in shielding were found.
TRANSMISSION/REFLECTION OF PLANE WAVES BY A CASCADE BLADE Rorl (NRC) The
propagation of sound waves through a subsonic blade row shows important reflection and cut-off effects with specific blade orientations and flow conditions. When the re-radiated vlave lengths are shorter than the blade chord length, the existing theoretical studies are difficult to assess because of the required lengthy numerical procedures. A two-dimensional cascade rig has therefore been designed (simulating a high hub to tip ratio rotor) for installation in the anechoic vlind tunnel facility. This model will permit the direct measurement of the reflected and transmitted wave
intensities for a range of incident waves and cascade flow conditions.
DIFFRACTION OF ARBITRARILY ORIENTED DIRECTIONAL SOURCES BY PLANAR BARRIERS (NRC) The completed analysis has been published in J. Acoust. Soc. ~merica,
Vol. 64, pp. 65-676. The associated abstract is as follows: An analysis has been carried out to determine the diffracted fields due to directional sources located near rigid planar screens with applicagion to the suppression of noise by acoustic barriers, especially highway barriers. Firstly, the diffracted field due to an arbitrarily oriented point dipole source is obtained by source position differentiation using the classical exact results due to McDonald. The dipole results are then combined with the monopole results to obtain the diffracted fields due to a series of combined sources having arbitrary directivity and orientation with respect to the plane of the screen. Diffraction results obtained in the present problem do not exhibit reciprocity with respect to source and observer locations. Typical computed insertion loss results are shown indicating the trends associated with source directionality, source orientation, and source loca-tion. Barrier insertion loss reductions, relative to those obtained with simple sources, are noted for vertically oriented directional sources located close to, and bel ow, the diffracting edge.
SOUND RADIATION FROM FINITE LENGTH CIRCULAR DUCTS (NRC) The sound radiation from an arbitrary acoustic source plane located inside a finite length
unflanged circular duct, including axial flow, has been formulated utilizing the Wiener-Hopf technique so as to include the results of earl ier radiation studies with semi-infinite length ducts. Approxi~late solutions have been obtained for the acoustic velocity potential both inside and outside the duct. Interference effects due to the finite duct terminations are obtained in the co~puted pressure field results. A technical note has been prepared and submitted for publication (see below) in which the radiation impedances for semi-infinite unflanged circular ducts with uniform axial flow are cal-culated as limiting cases of this more general study.
AIRFOIL NOISE RADIATION DUE TO TURBULENCE (NRC) A theoretical study of the noise radiation due to uniformly convecting turbulence past a finite span wing moving in a compressible subsonic airstream has been completed. The study divides into two parts: (i) the determination of the unsteady aero-dynamic loading due to the convecting turbulence, and (ii) the determination of the resulting dipole induced sound field. The power spectrum of the radiated sound in the far field is presently being computer (numerically) through the inversion of the integral equation for the aerodynamic loading on the wing.
IN-FLOW MICROPHONE MEASUREMENTS (NRC) A one-quarter inch Bruel and Kjaer
condenser microphone has been mounted in two small rectangular wings incor-porating a NACA 0012 section and having spans of 4.7 and 12.7 inches. The transducer was flush mounted in a region of laminar boundary layer in each case (zero incidence). The instrumented wings were placed in the Anechoic Wind Tunnel where self noise wh ere self noise data was taken over a series of flow velocities. Comparisons of the self noise levels measured from these airfoilS and those reported for the Bruel and Kjaer half-inch UA0386 nose cone indicated that considerable improvement has been obtained at high frequencies at the higher flow velocities (2.20 ft/sec).
SCATTERING OF A PLANE WAVE BY A HALF PLANE PLACED AT THE INTERFACE OF TWO
DIFPE~'NT SPEED FLOWS (NRC) The diffraction problem associated with a plane wave incident on a half plane placed at the interface of the two parallel flows with different constant velocities is being studied. The Wiener-Hopf technique (in particular, Jones' method) appears especially suited to this problem. A solution is expected which includes reflection and refraction effects due to the infinitesimally thin shear layer at the interface of the two different velocity flovls as well as the solid body diffraction due to the half plane.
RECENT PUBLICATIONS
1. W. G. Richarz, "Direct Correlation of Noise and Flow of a Jet Using Laser Doppler", UTIAS Report No. 230, June 1978.
2. H. S. Ribner, "Inferences of Source Coherence from Correlations of Jet Noise", Proc. 9th Internat. Congress on Acoustics, Madrid, July 4-9, 1977, p. E33.
3. H. S. Ribner, "TvlO-Point Correlations of Jet ~loise", J. Sound & Vibr., 56(1}, 1978, 1-19. (Condensation and slight revision of NASA TN D-8330, Dec. 1976.)
4. H. S. Ribner, "On the Role of the Shear Term in Jet Noise", J. Sound
&
Vibr., 52(1), 1977, 121-132.5. G. W. Johnston, K. Ogimoto, IIModal Radiation Impedances for Semi-Infinite
Unflanged Circular Ducts lncluding flow Effectsll
, Submitted (Aug. 1978)
and accepted for publication in Jour. of Sound
&
Vibration.6. G. H. Johnston, IIDiffraction of Arbitrary Oriented Directional Sources
by Rigid Planar Screensll
, Jour. Acoust. Soc. of America, Vol. 64(2),
Aug. 1978, 665-676.
7. A. A. Haasz, G. W. Johnston, IITraffic Background Level and Signal
Dura-tion Effects on Ai rcraft Noise Judger.Jentll
, Submitted for publ ication in
Jour. of Sound
&
Vibration (Sept. 1978).8. G. vJ. Johnston, IIThe Dynamics of a Curling Stonell
, Submitted and accepted
for publication by CASI Trans., Aug. 1978.
9. G. W. Johnston, N. D. E11is, B. Seshagiri, IIAerodynamic Interference
of High Speed Ground Vehicles", ASME Joint Fluids Engineering and CSME Conference, Montreal, ASME 74-FE-22.
10. G. W. Johnston, IIFan Rotor Noise - Some Recent Developmentsll
, Annual
CASI-AIAA Joint Meeting, Montreal, October 1973.
11. G. W. Johnston, D. Noble, IIHigh Frequency Discrete Noise Characteristics
of Unducted Rotors and Propellersll
, UTIAS Report No. 184, 1973.
12. B. Etkin, G. vJ. Johnston, H. vJ. Teunissen, 1I~1easurement of Turbulence
Inputs for V/STOL Approach Paths in a Simulated Planetary Boundary
Layerll
, UTIAS Report No. 189, July 1973.
13. G. ~J. Johnston, R. Carothers, IIAnnoyance Measurements Related to Urban
r~oise Exposurell
, Toronto-York Joint Program in Transportation, Research
Report ['~o. 13, Aug. 1973.
14. G. H. Johnston, R. Carothers, IIUrban Traffic fJoise Annoyance Measurements
and Derived Indicesll
, Toronto-York Joint Program in Transportation,
Research Report No. 24, Dec. 1974.
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AIR CUSHION TECHNOLOGY
Principal Investigators: P. A. Sullivan, J. S. ~Iansen
Co-Investigators: P. C. Hughes, A. J. Cousin
Res earch Engi neer: I. t1urra
Technician: J. Brandon
Ph.D. Student: t~. Hinchey
M.A.Sc. Students: A. Dupuis, P. V. Hartmann, D. Ribner
DEVEWPMENT OF THE UTIAS 43 11ETRE VIANETER AIR CUSHION VEHICLE TEST TRACK (NRC) The first circular UTIAS track, which was 6 metres in diameter, used a very light tether line. The large track allowed relatively sophisticated instrumentation such as accelerometers to be carried on the test vehicle, Vampire I. Originally, all sixteen data signals were transmitted simultane-ously along a signal cable attached to the tether cable, through a slip-ring assembly at the tether post, and then digitized and stored on magnetic tape by a computer. The resultant heavy cable introduced significant dynamics,
but it was decided to allow for this by measuring the cable force vector.
This year we have installed on Vampire I a system which simultaneously
samples the signals every 0.01 second, then digitizes and encodes theM for
transmission along a single small signal cable, and finally stores them on
the computer. It has greatly reduced cable effects.
DYNAMICS OF A SEGMENTED SKIRT CUSHION (NRC; Transport Canada3 Research and Development Centre - TDC) Both Vampi re land the cushi on dynami cs facil ity
have been equipped with a segmented skirt cushion similar to that manufactured by a Canadian company for use in a cross-river ferry in Alberta. Roll stiff-ness measurements are being made on the cushion dynamics facility, and the pitch-heave dynamics is being investigated on the circular track. We have
developed the computer program necessary for analysis of the noisy data from
the accelerometers and other transducers to obtain optimal estimates of
stiffness and damping. Our current objective is to identify the relative
importance of several possible sources of cushion damping.
INSTABILITIES OF AIR CUSHIONS (NRC; 'PVC) Analytical vJork3 has shovm that
even short ducts placed between the air supply fan and a plenum chamber can have a major effect on heave instabilities. In certain cases the effect is
similar to that of a Helmholtz resonator. Reference 3 describes the shape of
stability boundaries in the cushion pressure-cushion flow plane. This year, experimental confirmation was obtained by using the 12 metre diameter UTIAS
vacuum sphere as a large pneumatic capacitance to simulate an idealized
constant pressure fan. Excellent agreement between theory and experiment was
obtained, and a very large duct effect was demonstrated. Some analytical work on the effect of ducting on dynamic fan characteristics and on the prediction of amplitudes and frequencies of limit cycle oscillations has also been com-pleted in the past year.
INVESTIGATIONS OF PRESSURIZED MEMBRANE STRUCTURES (NRC; TDC) This work evolved
from our earl ier attempts to understand the roll hysteresis phenomenon.2 The
tapered conical cells in a multicell cushion buckle under certain conditions, and the destabilizing mechanism is internal asymmetrie pressure loading, not
skirt-ground friction. A "single wrinkle-creep" failure mode has been observed; this seems to be associated with the properties of the elastomer-fabric co~posite that is a typical skirt material • Theoretical analysis is continuing.
A COMPLIANT SURFACE GAS BEARING CONCEPT FOR RAPID LOADING AND UNLOADING OF HIGHWAY TRANSPORT TRAILERS (E. B. Eddy Forest Products) In this concept, the conventional load pallet is supported by two shoes which are made of a com-bination of eompliable materials and which are located so they are free to slide in two rigid shallow tracks built into the floor of the trailer. Air manifolds are located below the tracks, and air is fed to the shoe-traek interface by small suitably spaced holes. A ~odest flow rate reduees the effective friction to the point where a ~an can easily push a 1300 kg load. As is shown in the figure bel ow, the concept is used in the cushion dynamics
facility to provide a "frictionless" ground board for tests on a segmented cushion. Dur efforts in support of this Canadian innovation are intended to provide a basic understanding of the concept in terms of existing compliant surface gas bearing teehnology.
RECENT PUBLICATIONS (Not including UTIAS series)
1. P. 1\. Sullivan, G. J. Parravano, "Analysis of a Loop Type Flexible Skirted Cushion", CASI Jour., 23, 6, 1977, 346-358.
2. P. A. Sullivan, t,l, J. Hinchey, R. G. Delaney, "Statie Roll Stiffness Char-acteristics of Two t~ulticell Type Air Cushions", Jour. of Terramechanics, 15,1,1978,15-41.
3. M. J. Hinchey, P. A. Sullivan, "Duet Effects on the Heave Stability of Plenum Air Cushions", Jour. of Sound and Vibration, 60, 1, 1978, 87-99. 4. 11. J. Hinchey, P. 1\. Sull ivan, "Duet Effects on the Dynamic Fan
Character-isties of Air Cushion Systems" (Teehnical Note), Jour. of Hydronautics, to be published.
A segmented skirt is shown installed on the 2.44 m x 1.22 m dynamics facility. The cushion is resting on a ground board which in turn is supported by the type of air bearing used in the highway trailer project.
ENERGY TECHNOLOGY
Principal Investigators: J. H. de Leeuw, A. A. Haasz, P. C. Stangeby Research Scientist: P. L. Sears
Ph.D. Students Graduated: V. Chatoorgoon, W. T. Shmayda M.A.Sc. Students Graduated: I. Youle
M.A.Sc. Students: D. Davidson, L. Hebert, B. Lewis
FUSION ENERGY: GAS TARGET NEUTRON GENERATOR STUDIES (DSS; NRC; On tario
~nistry of Energy) The most serious engineering problem in fusion energy is the 14 MeV neutron damage which will be caused to reactor wall materials. Presently, there does not exist a source of 14 MeV neutrons of sufficient intensity to permit useful materials damage studies. The Institute is presently engaged in a major experimental and theoretical feasibility study on the intense 14 t1eV Gas Target Neutron Generator, GTNG, concept. The GTNG will incorporate an intense tritium ion beam, impacting on a high speed deuterium gas flow to give the D-T fusion reaction and th us 14 MeV neutrons. Because the gas target is self-cooled, self-replenishing and essentially indestructible, it can withstand enormous beam heat deposition and hence support very intense neutron generation.
The principal experimental requirement for GTNG studies is a large gas pumping system to operate the gas target. Fortunately the Institute is in possession of such a major installation, the Low Density Wind Tunnel, LDWT, p. 19. A wide variety of gas targets are conceivable with gas flow in the interaction zone subsonic, transonic or hypersonic. It is the long range purpose of the group to systematically explore the basic GTNG interactions and the operating properties, advantages and disadvantages of each target type. t4uch of the research to date was summarized in a recent review.! During the past year, preliminary experimental studies were completed on the convergent hypersonic gas target configuration2 and this work also
resulted in a joint publication with the U.S. gas target research group.3 Preliminary experimental studies were also completed on the particularly promising subsonic gas target.4,s Theoretical analysisG,7,a,9 centred on
the subsonic target which was shown to be the optimal configuration for most applications. Because of the complex nature of the hypersonic nozzle flow, flow visualization studies with the use of the schlieren technique are being performed.
FUSION ENERGY: PLASMA SURFACE INTERACTIONS (NRC; Ontario Ministry of
Energy; Dilworth~ Secord~ Meagher & Associates Ltd.) During the past year,
a new fusion research area has been started up, on the plasma surface inter-actions of interest to fusion reactor first-wall development. The Institute's large volume, ultra-high-vacuum, ultra-clean Space Simulator was originally designed to meet the exacting requirements of satellite-surface interaction research. These requirements turn out to be precisely those required in fusion surface studies. In addition, intense atomic hydrogen sources devel-oped for satellite research are being applied to study similar effects of importance in the fusion context. The same experimental set-up is being employed for carbon composite material studies of interest in satellite applications.
HYDROCARBON FUEL STUDIES (DSS; _E!4R; Alberta Oil Sands Technology and Research
Authority) Hydrocarbon fuels, when subjected to rapid devolatilization and
hydrogenation, are known to show different yields of gas and liquid products than i f these fuels are processed by traditional (slow) techniques. Both oil sand and coal have been tested10 in a rapid heating facility at UTIAS, capable of heating rat es up to 10,000 KIS and the products analysed by gas chromato-graphy. This work is aimed at the extraction of useful oil and gas products from oil sand and coal. The principal finding of the research to date is that total product yield is not a function of heat-up rate but is related primarily to the maximum temperature attained. The distribution of hydrocarbon products yielded, on the other hand, is very dramatically influenced by heating rate, with faster heating rates producing 1 ighter hydrocarbon products.
PLASMW CURRENT MULTIPLIER STUDIES (NRC) The Plasma Current Multiplier, PCM,
is a simple electrical gas discharge device which has the ability to amplify electrical current to very high values. An extensive study11 of the operating
properties of the PCr1 has been completed and the gain dependence on absolute current level and gas pressure has been elucidated for the first time. Appli-cations as a power cathode12 or as a current control device are under
examina-tion.
MHD pm/ER GENERATION (NRC) Magnetohydrodynamic U~HD} power generation is a
potential replacement for both the steam turbine and electrical generRtor for heat-electricity conversion. Studies have been undertaken on a promising MHD variant involving H2-02 combustion. 13
RECENT PUBLICATIONS
1. J. H. de Leeuw, A. A. Haasz, P. C. Stangeby, "Canadian Gas Target rJeutron Generator Research", Nucl. Instrum. & t~eth., 145, 1977, 119. 2. J. H. de Leeuw, A. A. Haasz, P. C. Stangeby, I. S. Youle, "Experimental
Simulation of a Hypersonic Gas Target Neutron Generator for Fusion Materials Studies", AIAA J. of Energy, 2, 1978, 238.
3. S. C. Johnston, A. A. Haasz, P. C. Stangeby, "Comparison of Experimental Results of Gas Target Neutron Generator Simulation Studies", AIAAJ . of Energy, 2, 1978, 253.
4. A. A. Haasz, P. C. Stangeby, I. S. Youle, "Experimental Tests of Subsonic Gas Target", to be submitted to AlAA J. of Energy.
5. I. S. Youle, "Experimental Tests of Subsonic Gas Target", r'.1.A.Sc. Thesis, UTIAS, October 1978.
6. P. C. Stangeby, V. Chatoorgoon, "Subsonic Gas Target", AIAA J. of Energy 1,1977,387.
7. V. Chatoorgoon, P. C. Stangeby, "Subsonic Gas Target 14 MeV Neutron Generator" , AIAA J. of Energy 2, 1978, 129.
8. V. Chatoorgoon, P. C. Stangeby-; "Start-Up and Stability of Subsonic Gas Targets 11 , AIAAJ. of Energy, 2,1978,254.
9. V. Chatoorgoon, "Gas Target r'leutron Generator Studies", Ph.D. Thesis, UTIAS, October 1978.
10. P. C. Stangeby, P. L. Sears, "Total Yields of Heated Dil Sand", in Dil Sand and Oil Shale Chemistry, Ed. O. P. Strausz and E. ~·1ilown, Verlag Chemie Int., 1978, 101-118.
11. H. T. Shmayda, "The Plasma Current Multiplier", Ph.D. Thesis, UTIAS, October 1978.
12. P. C. Stangeby, W. T. Shmayda, "DC Plasma Production ~Jithout Electron Emission", Rev. Sci. Instrum., 47, 1976, 935-937.
13. P. C. Stangeby, "Comparative Economics for H2-02 Emergency and Peaking Power Production " , Proc. Sixth Int. MHD Conf., Washington, June 9-13, 1975 (ERDA, etc).
FLIGHT TRANSPORTATION
Principal Investigator: L. D. Reid Co-Investigator: H. S. Ribner
Research Scientists: IL O. Graf,
A.
M. BillingM.A.Sc. Students: A. Gakwaya,
B.
Lay, A. B. Markov, E. Solowka AIRCRAFT RESPONSE TO WIND SHEAR AND TURBULENCE DURING THE LANDING APPROACH(AFFDL; AFOSR; AES; NRC) With the advent of STOL flight transportation systems and their proposed operation into city-centre STOL ports, there is an increased interest in aircraft response to wind shear and turbulence during the landing approach. Our present work has been aimed at studying the longitudinal response of a typical STOL aircraft to both wind shear and turbulence. Various techniques have been compared (flight path corre-lations, power spectral density, equivalent deterministic variable and time series solution) and several sourees of wind data employed (wind tunnel, flight data and atmospheric models). Work is in progress that studies the dynamic response of aircraft flying curved approach profiles in conditions
of wind shear. This includes a study of techniques for generating
worst-ease wind shear time and position histories. Another aspect of this work
is the development of a program th at will permit the evaluation of autopilot models, which will assist in landing a STOL aircraft. The manned simulator
is used to study the behaviour of pil ots 1 anding a STOL aircraft through wind shear and the effeetiveness of predictive information on the wind
shear on their landing performance.
THE DEVELOPMENT OF A GENERAL PURPOSE MANNED SIMULATION FACILITY (NRC) In order to further our capacity to study both human performance and the inter-action between man and machine we have continued to improve our general purpose simulation facility. In a typical application much of the vehicle dynamics are implemented on a TR-48 analog computer. The HP 2100A digital computer is used to generate a display and to assist the analog computer. The display facing the operator can be either a small screen (33 cm diagonal) or a large screen display (213 cm diagonal) driven by the digital computer. Work is proceeding on improving the quality of the image projected on the screen. The work station can be configured to represent the system under study. Recent simulations have included an air cushion vehicle and remote manipulator arm. Currently experiments are under way which use the simulator either as a STOL aircraft landing tt1rough wind shear or an automobile being driven on a road with various curves.
THE OPERATION AND PERFORMANCE OF CARS AND TRUCKS (MTC) A project completed recently involved a study of an instrumentation and recording system that could be installed in vehicles to get a comprehensive record of operating conditions and engine performance under actual road driving conditions. The system would monitor 24 parameters covering engine and drive train, vehicle performance and atmospheric and road conditions. A project underway at the moment involves the validation of car driver models. Here the gener-al
purpose simulation facility is being configured to represent the car driving task. Experimental data will be taken fr om this facility and used to check out the predicted performance derived from the driver models.
TRANSONIC PROPELLER There has been a resurgence of interest in high speed propellers af ter two decades of dominanee by jet propulsion. Thus it has
