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Laminar How Control (1976- 1982) NASA T" 84496 NASATechnical Memomdm 844% c.1 Laminar How Control (1976-1982) A Selected, Annotated Bibliography Marie H. Tuttle and Dal V. Maddalon AUGUST 1982 " . .. - " NASA NASATechnical Memorandm -% Laminar flow Control (1976-1982) A Selected, Annotated Bibliography Marie H. Tuttle and Dal V. Maddalon Langley Research Center Hampton, Virginia National Aeronautics and Space Administration Scientlflc and Technlcal Information Branch \. i ” INTRODUCTION .................................................................... 1 BIBLIOGRAPHY (1976-1982) ........................................................ 3 APPENDIX ........................................................................ 65 ENTRIES WITH PUBLICATIONDATES PRIOR TO 1976 .................................... 66 AUTHOR INDEX .................................................................... 76 iii INTRODUCTION Laminar Flow Control (LFC) technologydevelopment has undergone tremendous progress in recent years as focused research efforts in materials, aerodynamics, systems,and structures have begun to pay off. A virtualexplosion in the number of research papers published on this subject has occurred since interest was first stimulated by the 1976 introduction of the NASA's Aircraft EnergyEfficiency Laminar Flow Control (ACEE/LFC) Program.Today, a wide variety of fundamentaland applied researchprograms exist, not only in controlled (active) boundary-layer flow, but alsoin natural (passive) laminar flow. Studies of airfoils whichcombine the two methods (hybrid) are now beginning. The purpose of this selected bibliography is to list available, unclassified laminarflow research completed since the ACEE/LFC Program was begun. This bibliography is therefore limited to researchconducted from about 1975 to mid 1982. The reports listed hereinemphasize the aerodynamics and systems studies which were the main product of this work, but some structuresreports are also included. Aerodynamic research is mainly limited tothe subsonic and transonicspeed regimes. Becausewind-tunnel flow qualities such as free stream disturbancelevel play such an important role in boundary-layertransition, much researchhas recently been done in this area and it is also included. Laminarflow controlresearch through 1978 was extensivelysurveyed in NASA RP-1035 (citation 141). Some pertinentpublications from thatreference are also includedhere. In addition, there is available a bibliography(citation 7) of Air ForceFlight Dynamics Laboratory (AFFDL) reports on LFC whichsummarizes work accomplishedduring the X-21 program. A third LFC bibliography(citation 25) has been published by Lockheed-Georgia. The appendixof this compilation includes reports published prior to 1976 which were not included in NASA "1035 but are pertinent to this subject. Considerable effort was made to survey as mch relevant literature as possible from many differentsources. However, some importantpapers may havebeen inadvertentlyoverlooked. Personswishing more information on specific topics shouldcheck the reference lists in those documentsdescribed herein which are pertinent to their interest. They also are urged to use the services available from NASA for computerdata bank searches.Technical libraries at NASA researchcenters can fill such requests. The items selected for inclusion in this bibliography are generallyarranged chronologically by date of publication.Conference papers, however, are placed accordingto date of presentation. An authorindex is included at the endof the bibliography. In most cases, abstracts used are from the NASA announcement bulletins "Scientificand Technical Aerospace Reports" (STAR) and"International Aerospace Abstracts" (IAA). Inother cases, authors' abstracts were used. License was taken to modify or shorten abstracts. If it is known that a paper hasappeared in several forms,mention is made of this fact. Identifyinginformation, including accession and report numbers(when known), is included in the citations in order to facilitate the filling of requests for specific items. When requesting material fromyour library orother Source, it is advisable to includethe complete citation;the abstract may be omitted. A 11#11 after an accession number indicates that the document is also available in microfiche form. Availability sources of thedieferent types of materials are given below: Accession Number Type of Material Where Obtained Axx-xxxxx Published literature American Institute ofAeronautics in journals or andAstronautics Example: conferences, etc., TechnicalInformation Service A75-25583 as indicated. 555 West 57th Street, 12thFloor New York, NY 10019 AIAA-82-0567 AI- Papers NXX-XXXXX ReportTechnical Nationalliterature unlessanother source InformationService (NTIS) Example: is given in the 5285 Port Royal Road N67-37604 citation Springfield, VA 22 16 1 xxx-xxxxx Reportliterature having NASA Scientific and some type of limited TechnicalInformation Example: distribution. Facility(STIF) X72-76040 P.O. Box 8757 B.W.I. Airport, MD 21240 Theses may be ordered by Order Number from University Microfilms A Xerox Company 300 North Zeeb Road Ann Arbor, Michigan 48106 Any others - Ask yourlibrary, or NASA Scientific and Technical include any InformationFacility (STIF) information P.O. Box 8757 given B.W.I. Airport, MD 21240 2 BIBLIOGRAPHY 1. Aircraft Fuel ConservationTechnology. transport. The feasibility of hydrogen-fueled *Task forcereport. NASA TU-X-74295, Sept.9, aircraft is discussed. 1975, 141 pp. *StanfordUniv., Stanford, Calif. N77- 11055# An advancedtechnology program is described 4. *Zuda, E.: Installation ofa Flow Straightener forreduced fuel consumption in air transport. inthe Subsonic Wind Tunnel. DFVLR-Nachrichten, Costbenefits and estimates are givenfor improved NOV. 1975, pp.697, 698. (In German. 1 enginedesign and components, turboprop propulsion systems,active control system, laminar flow A76- 13407 control, andcomposite primary structures. Turbulence-produceddisturbances in wind *NASA, Washington, D.C. tunnelexperiments led to the installation of a flow-straighteningdevice. The eliminationof turbulenceeffects in such a device is obtained by 2. *Canu, M.: Noiseand Turbulence in Transonic dividingthe area of theflow cross section into a Wind Tunnels.Report No. AAAF-NF76- 12; number of separatechannels. The use of cylindri- ISBN-2-7170-0390-8; Paris Assoc. Aeron. et caltubes for this purpose has certain disadvan- Astronautiquede France. Presented atthe 12th tages. It was, therefore,decided to employ EcoleNatl. Super. de Mecan. et d'Aerotech./CEAT regularhexagonal pipes for the design of theflow Colloq.d'Aerodyn. Appl., Poitiers,France, straightener. Aluminum pipes were selected 5-7Nov. 1975, 21 pp. (InFrench.) because of their low weight.Details concerning thedesign and theinstallation of thedevice are N77- 10082# discussed. Reduction of noisein transonic wind tunnels, *DeutscheForschungs- und Versuchsanstaltfuer due largelyto wall perforations, was studied. Luft- und Raumfahrt. Zentralabteilung Different types of perforations were tested. Niedergeschwindigkeits-Windkanaeale, Porz-Wahn, Several of thesebring the noise level down to West Germany. that of guidevanes. The measurements were made withmicrophones or with hot wire probes;from the analogy of thespectra obtained it was concluded 5. *Bauer,Frances; *Garabedian, Paul; *Korn, thatnoise is themajor componentof the David;*Jameson, Antony; fBeckmann, M., ed.; turbulence. andfKuenzi, H. P., ed.: Supercritical Wing Sections 2, Volume 108. NASA CR-142229, 1975, +OfficeNational d' Etudes et deRecherches 301 pp. Springer-Verlag, 1975. Aerospatiales (ONERA), Modane, France N75- 18167 3. *Shevell, R. S.: Advanced SubsonicAircraft - A mathematicaltheory for the design and The TechnologicalResponse toFuture Air Trans- analysis of supercritical wing sections was previ- portation Needs. In:Princeton Univ. Conference ouslypresented. Examplesand computer programs Proceedings(A76-457761, Princeton, N-J., NOV- 10, showing how this method workswere included. The 11,1975, pp. 5-1 to 5-26. workon transonics is presentedin a more definitive form.For design, a better model of A76-45781# the trailing edge is introduced whichshould eliminate a loss of fifteenor twenty percent in Improvements,such as automaticflight mn- lift experiencedwith previous heavily aft loaded agement,advanced aerodynamics, laminar flow con- models, which is attributedto boundarylayer trol, advancedengines, and advanced structural separation. How dragcreep can be reduced atoff- materials, couldlead to significant reductions in designconditions is indicated. A rotatedfinite fuelrequirements; the development of new tech- difference scheme is presentedthat enables the nologies is, however,dependent on the economic application of Murman'smethod of analysis in health of theaviation industry. The historyof more or less arbitrarycurvilinear coordinate transport aircraft is reviewedas are technolog- systems. This allows the use of supersonic as icaladvances - dragreduction, weight reduction, well assubsonic free stream Mach numbers and to improvement inlift coefficient, etc. Some devel- capture shock waves as far back on an airfoil as opments in air transportation which raised great desired.Moreover, it leads to an effectivethree expectations,but have failed to have a signifi- dimensionalprogram for the computation of tran- cantimpact are reviewed: laminar flow control, sonicflow past an oblique wing. In thecase of nuclear powered aircraft, STOL andthe supersonic two dimensionalflow, the method is extendedto
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