DOCSLIB.ORG

;• National Advisory Committee for Aeronautics

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
;• National Advisory Committee for Aeronautics I , / ;• NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS REPORT No. 777 THE THEORY OF PROPELLERS Ill-THE SLIPSTREAM CONTRACTION WITH NUMERICAL VALUES FOR TWO-BLADE AND FOUR-BLADE PROPELLERS By THEODORE THEODORSEN 1944 For sale by the Superintendent of Documents - U. S. Government Printing Office - Washington 20, D. C. - Price 20 cents -S.- AERONAUTIC SYMBOLS 1. FUNDAMENTAL AND DERIVED UNITS Metric English Symbol Unit Abbrevia- Abbrevia- uunit t tion Length 1 meter--------------------m foot (or mile) --------- -ft (or mi) Time -------- --t second ----------------- --s second (or hour) ------- --see (or hr) Force---------- F weight of 1 kilogram kg weight of 1 pound-------lb Power ------- - P horsepower (metric) ----- --------— horsepower-------------hp Speed v f kilometers per hour--------kph miles per hour ---------- mph imeters per second ------- -mps feet per second--------- fps 2. GENERAL SYMBOLS W Weight=mg V Kinematic viscosity g Standard acceleration of gravity=9.80665 rn/s 2 p Density (mass per unit volume) or 32.1740 ft/sec' Standard density of dry air, 0.12497 kg-m-'-s' at 15° 0 W M Mass= — and 760 mm; or 0.002378 lb-ft-4 sec' g Specific weight of "standard" air, 1.2255 kg/ml or I Moment of inertia=mk2. (Indicate axis of 0.07651 lb/cu ft radius of gyration k by proper subscript.) Coefficient of viscosity 3. AERODYNAMIC SYMBOLS S Area ill Angle of setting of wings (relative to thrust line) S. Area of wing it Angle of stabilizer setting (relative to thrust 6' Gap line) b Span (7 Resultant moment C Chord Resultant angular velocity V vi A Asp, ect ratio, B Reynolds number, p— where 1 is a linear dimen- V True air speed sion (e.g., for an airfoil of 1.0 ft chord, 100 mph, 1 q Dynamic pressure, 2p standard pressure at 15° C, the corresponding Reynolds number is 935,400; or for an airfoil in L Lift, absolute coefficient (YL= L of 1.0 chord, 100 mps, the corresponding gS Reynolds number is 6,865,000) D Drag, absolute coefficient a Angle of attack Angle of downwash D0 Profillrag, absolute coefficient D Angle of attack, infinite asjiect ratio qS at Angle of attack, induced D1 Inducirag, absolute coefficoefficient C=- a Angle of attack, absolute (measured from zero- lift position) 0=D,, D Parasi drag, absolute coefficient '1 Flight-path angle 0 Cross- ud force, absolute coefficient qS ERRATUM NACA REPORT No. 777 THE THEORY OF PROPELlERS III - THE SLIPSTREAM CONTRACTION WITH NUMERICAL VALUES FOR NO-BLADE AND FOUR BLADE PROPELLERS By Theodore Theoclorsen 194 Page 18, figure 7(a): The bottom part of the lowest curve In tIre lower left-hand corner of the figure should. be - - Instead. of - J/1 w1 vw REPORT No. 777 THE THEORY OF PROPELLERS Ill-THE SLIPSTREAM CONTRACTION WITH NUMERICAL VALUES FOR TWO-BLADE AND FOUR-BLADE PROPELLERS By THEODORE THEODORSEN Langley Memorial Aeronautical Laboratory Langley Field, Va. I t ft LM National Advisory Committee or A&onauüi' IIwlpIa1trs, 1500 New Hampshire Avenue NW., Washington . P. C. Created by act of Congress approved Mareli 3. 1915, for the supervision and dir'Cl ion of ti ientific stud v of the problems of flight (1]. S. Code, title 49, sec. 241). Its membership \\'tis ierea'i1 to 1. v act approv'd March 2, 1929. The members are appointed by the President, and serve as -uch without CompisJtion. JEROME C. IIcSSAKER, Sc. I)., Cambridge, Mass.. Ci',non LYMAN J. BRIGOS, Ph. D., Fire Chairman, Director. National AUIIREY W. FITCH, ViceAdiniral, United States Nav y . Deputy Bureau of Standards. Chief of Operations (Air). Navy Depart iiient. CHARLES G. ARBOT, Sc. D., Vice Chairman, Executive Committee, WILLIAM LITTLEWOOD, M. E.. Jackson IJeihts, Long Island. N.Y Secretary, Smithsonian Institution. HENRY H. ARNOLD, General, United States Army, Commanding FRANCIS W. REICHELDERFER, Sc. D.. (hief, Ututel states General, Arm y Air Forces, War Department. Weather Bureau. WILLIAM A. M. BURDEN, Special Assistant to the Secretar y of LAWRENCE B. RICHARDSON, Rear Admiral United States Navy, Commerce. Assistant Chief, Bureau of Aeronautic- Nav y DepartIII('nt VANNE VAR BUS H, Sc. D., Director, Office of Scientific Research EDWARD WARNER, Sc. D., Civil Aeronain cs Board, Washing- and Development, Washington, D. C. ton, D. C. WILLIAM F. DIJRAND, Ph. D., Stanford Universit y , California. ORVILLE WRIGHT, Sc. P., Dayton, Ohio. OLIVER P. ECH0I.S, Major General, United States Arm y , Chief of Maintenance, Materiel, and Distribution, Arm y Air Forces, THEODORE P. WRIGHT, Sc. D., Administrator of Civil Aero- War Department. nautics, Department of Commerce. GEORGE W. LEWIS, Sc. D., Director of Aeronautical Research JOHN F. VICTORY, LL. M., Secretary HENRY J. E. REID, Sc. D., Engineer-in-Charge, Langley Memorial Aeronautical Laboratory, Langley Field, Va. SMITH J. DEFRANCE, B. S., Engineer-in-Charge, Ames Aeronautical Laboratory, Moffett Field, Calif. EDWARD R. SHARP, LL. B., Manager, Aircraft Engine Research Laborator y, Cleveland Airport, Cleveland, Ohio CARLTON KEMPER, B. S., Executive Engineer, Aircraft Engine Research Laborator y, Cleveland Airport, Cleveland, Ohio TECHNICAL COMMITTEES AERODYNAMICS OPERATING PROBLEMS POWER PLANTS FOR AIRCRAFT MATERIALS RESEARCH COORDINATION AIRCRAFT CONSTRUCTION Coordination of Research Needs of Military and Civil Aviation Preparation of Research Programs Allocation of Problems Prevention of Duplication LANLiLY ML\IORIAL,AERONAITICAL LABORATORY ÂMES AER0\ \ITICAL LABORATORY Langley Field, Va. MoTh r Field. Calif. ,('RAFT ENGINE RESEARCH LABORATORY, Cleveland Airport, Cleveland, Ohio unified control, for all agencies, of scientific research on the fundamental problemsI of jug/if IFICE OF AERONAUTICAL INTELLIGENCE, Washington, P. C. I st a aipilcif ion, and dissemination of scientific and technical information on aeronautics II REPORT No. 777 THE THEORY OF PROPELLERS Ill-THE SLIPSTREAM CONTRACTION WITH NUMERICAL VALUES FOR TWO-BLADE AND FOUR-BLADE PROPELLERS By THEODORE THEODORSEN SUMMARY x ratio of radius of element to tip radius of vortex As the conditions of the ultimate wake are of concern both sheet (r/R) theoretically and practically, the magnitude of the slipstream yR radial velocity contraction has been calculated. It will be noted that the con- V advance velocity of propeller traction in a representative case is of the order of only 1 percent w rearward displacement velocity of helical vortex surface of the propeller diameter. In consequence, all calculations - w need involve only first-order effects. Curves and tables are given w=V for the contraction coefficient of two-blade and four-blade pro- number of blades pellers for* various valves of the advance ratio; the contraction p coefficient is defined as the contraction in the diameter of the mass coefficient wake helix in terms of the wake diameter at infinity. The contour lines of the wake helix are also shown at four values of x (F7rV?KU) the advance ratio in comparison with the contour lines for an F circulation at radius infinite number of blades. fpFw- INTRODUCTION circulation function for single rotation K (x) 2xVw Since reference is often made to the wake infinitely far behind the propeller, it is desirable to establish certain angular velocity of propeller, radians per second relationships between the dimensions, of the propeller and due to a douhlet'element at those of the wake helix at infinity. The present paper con- y' radial velocity' at point P O,x except for a-constant factor siders the relationship of the propeller diameter and the wake diameter, or the problem of the slipstream contraction. ( [0 cos (0+r) —sin (0+ T)] [1-2x2+X202+x cos (0+r)] The discussion is restricted to a consideration of first-order [1+x2+X202 -2x cos (O+r)] effects, that is, to the determination of the contraction per K(x).. unit of loading for infinitely small loadings only. It will be y2 =—y1 wherenr=O, 1, 2, . pl seen that the contractions are indeed very small, of the order of a few percent of the propeller diameter, and that the high-order terms are therefore not of concern. The inter- • Y1 =f y2 dx ference velocity accordingly • is neglected as small compared with the stream velocity. The wake helix lies on a perfect Y2 angle of contraction, except for a constant cylinder and the pitch angle is everywhere the same. It is noted that the assumption of zero loading corresponds to factor (2=J Y1 do) that used by Goldstein for a different purpose. • contour line of contraction, except for a constant SYMBOLS R tip radius of propeller factor'(Yi=fYido) r radius of element of vortex sheet r0 '- Ic3 X3 r contraction - total contractioni n terms of radius - \KI r0 total contraction or contraction at =O Pc • /x37 angle between starting point of spiral line and point Rc3- contraction coefficient (-4 11 3) H pitch of spiral 0 angular coordinate on vortex sheet = sin {tan(x - x )E(k) + x32[F(k) -E(k)IJ hH— - X advance ratio () wi =[(j_ k) F(k)_-yE(k)]' 1 2 REPORT NO. 777—NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS THEORY By introducing the nondimensional quantities The radial velocity is obtained by using the Blot-Savart H law and integfating over the entire surface of discontin- IrR uity. If ArG is the total contraction, the problem is to deter- (2) - mine the ratio for various numbers of blades at several F advance ratios. Simple expressions referring to zero load- ing are used throughout. in the Biot-Savart law, the following expression is obtained The radial inward velocity dvR' at the point P is calculated. for the radial inward velocity dvR' due to an element on (See figs. 1' and 2.) This velocity results from an element the wake helix of strength f: ü cos (O+r) —sin (o +7-) (3) 4ir R [1+x2+X282-2x cos (0+T)] By differentiatiiig equation (3) with respect to x, the field of a doublet element on the helical vortex sheet is obtained, the doublet element consisting of two neighboring singlet elements each of strengthf.
Load more

Recommended publications
  • Comparison of Theodorsen's Unsteady Aerodynamic Forces with Doublet Lattice Generalized Aerodynamic Forces 5B
    NASA/TM–2017-219667 Comparison of Theodorsen’s Unsteady Aerodynamic Forces with Doublet Lattice Generalized Aerodynamic Forces Boyd Perry, III Langley Research Center, Hampton, Virginia September 2017 NASA STI Program . in Profile Since its founding, NASA has been dedicated to the x CONFERENCE PUBLICATION. advancement of aeronautics and space science. The Collected papers from scientific and technical NASA scientific and technical information (STI) conferences, symposia, seminars, or other program plays a key part in helping NASA maintain meetings sponsored or co-sponsored by NASA. this important role. x SPECIAL PUBLICATION. Scientific, The NASA STI program operates under the auspices technical, or historical information from NASA of the Agency Chief Information Officer. It collects, programs, projects, and missions, often organizes, provides for archiving, and disseminates concerned with subjects having substantial NASA’s STI. The NASA STI program provides access public interest. to the NTRS Registered and its public interface, the NASA Technical Reports Server, thus providing one x TECHNICAL TRANSLATION. of the largest collections of aeronautical and space English-language translations of foreign science STI in the world. Results are published in both scientific and technical material pertinent to non-NASA channels and by NASA in the NASA STI NASA’s mission. Report Series, which includes the following report types: Specialized services also include organizing and publishing research results, distributing x TECHNICAL PUBLICATION. Reports of specialized research announcements and feeds, completed research or a major significant phase of providing information desk and personal search research that present the results of NASA support, and enabling data exchange services. Programs and include extensive data or theoretical analysis.
    [Show full text]
  • FLUID DYNAMICS, Volume IV
    http://dx.doi.org/10.1090/psapm/004 PROCEEDINGS OF SYMPOSIA IN APPLIED MATHEMATICS VOLUME IV FLUID DYNAMICS McGRAW-HILL BOOK COMPANY, INC. NEW YORK TORONTO LONDON 1953 FOR THE AMERICAN MATHEMATICAL SOCIETY 80 WATERMAN STREET, PROVIDENCE, RHODE ISLAND PROCEEDINGS OF THE FOURTH SYMPOSIUM IN APPLIED MATHEMATICS OF THE AMERICAN MATHEMATICAL SOCIETY Held at the University of Maryland June 22-23, 1951 COSPONSORED BY THE U.S. NAVAL ORDNANCE LABORATORY M. H. Martin EDITOR EDITORIAL COMMITTEE R. V. Churchill Eric Reissner A. H. Taub Copyright, 1953, by the McGraw-Hill Book Company, Inc. Printed in the United States of America. All rights reserved. This book, or parts thereof, may not be reproduced in any form without permission of the publishers. Library of Congress Catalog Card Number: 52-10326 CONTENTS EDITOR'S PREFACE v Some Aspects of the Statistical Theory of Turbulence 1 BY S. CHANDRASEKHAR A Critical Discussion of Similarity Concepts in Isotropic Turbulence 19 BY C. C. LIN The Nonexistence of Transonic Potential Flow 29 BY ADOLF BUSEMANN On Waves of Finite Amplitude in Ducts (Abstract) 41 BY R. E. MEYER On the Problem of Separation of Supersonic Flow from Curved Profiles .... 47 BY T. Y. THOMAS On the Construction of High-speed Flows 55 BY G. F. CARRIER AND K. T. YEN An Example of Transonic Flow for the Tricomi Gas 61 BY M. H. MARTIN AND W. R. THICKSTUN On Gravity Waves 75 BY A. E. HEINS Hydrodynamics and Thermodynamics 87 BY S. R. DE GROOT Nonuniform Propagation of Plane Shock Waves 101 BY J. M. BURGERS Theory of Propellers 109 BY THEODORE THEODORSEN Numerical Methods in Conformal Mapping 117 BY G.
    [Show full text]
  • Interviw with Homer J. Stewart
    HOMER J. STEWART (1915 - 2007) INTERVIEWED BY JOHN L. GREENBERG October-November 1982 INTERVIEWED BY SHIRLEY K. COHEN November 3, 1993 1979 ARCHIVES CALIFORNIA INSTITUTE OF TECHNOLOGY Pasadena, California Subject area Engineering, aeronautical engineering Abstract Two interviews with Homer J. Stewart, aeronautical engineer and Caltech Professor of Aeronautics, 1942-1980, and Caltech alumnus (PhD, 1940). The interview by John L. Greenburg is in four sessions in October and November of 1982. A supplemental interview was conducted by Shirley K. Cohen in November 1993. The first interview covers Stewart’s youth and education (B.Aero.E., University of Minnesota, 1936) and his early interest in aeronautic technology. Comes to Caltech for graduate study in aeronautics, 1936-1940 (PhD, 1940); courses with faculty members W. Smythe, R. C. Tolman, E. T. Bell, M. Ward, H. Bateman. Comments on critical roles of Theodore von Kármán and Clark Millikan in establishment of graduate program known as GALCIT [Guggenheim Aeronautical Laboratory at the California Institute of Technology]; creation of GALCIT wind tunnel for testing; advancement of aeronautical engineering education; and linking of GALCIT to burgeoning California aerospace industry. Von Kármán’s identification of new technologies; his bridging of industry and http://resolver.caltech.edu/CaltechOH:OH_Stewart_H academe; similar integrating approach applied to founding of Jet Propulsion Laboratory [JPL]. Discusses GALCIT’s role in the development of commercial aviation in the 1930s. Appointment to professorial rank (1942) and wartime teaching and research on meteorology; comments on Irving Krick at Caltech. Discusses beginnings of rocketry at Caltech and his own pioneering contributions; work of Frank Malina and H.
    [Show full text]
  • Theodorsen's and Garrick's Computational
    https://ntrs.nasa.gov/search.jsp?R=20200002621 2020-05-24T04:40:06+00:00Z THEODORSEN’S AND GARRICK’S COMPUTATIONAL AEROELASTICITY, REVISITED Boyd Perry, III Distinguished Research Associate Aeroelasticity Branch NASA Langley Research Center Hampton, Virginia, USA International Forum on Aeroelasticity and Structural Dynamics Savannah, Georgia June 10-13, 2019 “Results of Theodorsen and Garrick Revisited” by Thomas A. Zeiler Journal of Aircraft Vol. 37, No. 5, Sep-Oct 2000, pp. 918-920 Made known that – • Some plots in the foundational trilogy of NACA reports on aeroelastic flutter by Theodore Theodorsen and I. E. Garrick are in error • Some of these erroneous plots appear in classic texts on aeroelasticity Recommended that – • All of the plots in the foundational trilogy be recomputed and published 2 “Results of Theodorsen and Garrick Revisited” by Thomas A. Zeiler Journal of Aircraft Vol. 37, No. 5, Sep-Oct 2000, pp. 918-920 Made known that – • Some plots in the foundational trilogy of NACA reports on aeroelastic flutter by Theodore Theodorsen and I. E. Garrick are in error • Some of these erroneous plots appear in classic texts on aeroelasticity Recommended that – • All of the plots in the foundational trilogy be recomputed and published Cautioned that – • “One does not set about lightly to correct the masters.” 3 Works Containing Erroneous Plots 1. Theodorsen, T.: General Theory of Aerodynamic Instability and the Mechanism of Flutter. NACA Report No. 496, 1934. 2. Theodorsen, T. and Garrick, I. E.: Mechanism of Flutter, a Theoretical and Experimental Investigation of the Flutter Problem. NACA Report No. 685, 1940. 3. Theodorsen, T.
    [Show full text]
  • Theodorsen's and Garrick's Computational
    THEODORSEN’S AND GARRICK’S COMPUTATIONAL AEROELASTICITY, REVISITED Boyd Perry, III Distinguished Research Associate Aeroelasticity Branch NASA Langley Research Center Hampton, Virginia, USA International Forum on Aeroelasticity and Structural Dynamics Savannah, Georgia June 10-13, 2019 “Results of Theodorsen and Garrick Revisited” by Thomas A. Zeiler Journal of Aircraft Vol. 37, No. 5, Sep-Oct 2000, pp. 918-920 Made known that – • Some plots in the foundational trilogy of NACA reports on aeroelastic flutter by Theodore Theodorsen and I. E. Garrick are in error • Some of these erroneous plots appear in classic texts on aeroelasticity Recommended that – • All of the plots in the foundational trilogy be recomputed and published 2 “Results of Theodorsen and Garrick Revisited” by Thomas A. Zeiler Journal of Aircraft Vol. 37, No. 5, Sep-Oct 2000, pp. 918-920 Made known that – • Some plots in the foundational trilogy of NACA reports on aeroelastic flutter by Theodore Theodorsen and I. E. Garrick are in error • Some of these erroneous plots appear in classic texts on aeroelasticity Recommended that – • All of the plots in the foundational trilogy be recomputed and published Cautioned that – • “One does not set about lightly to correct the masters.” 3 Works Containing Erroneous Plots 1. Theodorsen, T.: General Theory of Aerodynamic Instability and the Mechanism of Flutter. NACA Report No. 496, 1934. 2. Theodorsen, T. and Garrick, I. E.: Mechanism of Flutter, a Theoretical and Experimental Investigation of the Flutter Problem. NACA Report No. 685, 1940. 3. Theodorsen, T. and Garrick, I. E.: Flutter Calculations in Three Degrees of Freedom. NACA Report No. 741, 1942.
    [Show full text]
  • Aeronautical Science 101: the Development of Engineering Science in Aeronautical Engineering Education at the University of Minnesota
    Aeronautical Science 101: The Development of Engineering Science in Aeronautical Engineering Education at the University of Minnesota A THESIS SUBMITTED TO THE FACULTY OF THE GRADUATE SCHOOL OF THE UNIVERSITY OF MINNESOTA BY Amy Elizabeth Foster IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF ARTS October 2000 1. Introduction: Engineering Science and Its Role in Aeronautical Engineering Education In 1929, the University of Minnesota founded its Department of Aeronautical Engineering. John D. Akerman, the department head, developed the curriculum the previous year when aeronautical engineering was still an option for mechanical engineering students. Akerman envisioned the department's graduates finding positions as practical design engineers in industry. Therefore, he designed the curriculum with a practical perspective. However, with the rising complexity of aircraft through the 1930s, 40s, and 50s, engineering science grew more important to aeronautical engineering design practices than ever before. In 1948, the university closed a deal on an idle gunpowder plant. The aeronautical engineering department converted the site into a top- notch aeronautical research laboratory. A new dean for the engineering schools, Athelstan Spilhaus, arrived at the University of Minnesota in 1949. He brought a vision for science-based engineering. Akerman, who never felt completely comfortable with theoretical design methods, struggled with the integration of engineering science into his department's curriculum. Despite Akerman's resistance, engineering science eventually permeated the aeronautical engineering curriculum at Minnesota through this new lab and the dean's vision. In following this path, the University of Minnesota came to exemplify the significant place of engineering science in aeronautical engineering by the 1950s.
    [Show full text]
  • Theodorsen's and Garrick's Computational
    International Forum on Aeroelasticity and Structural Dynamics IFASD 2019 9-13 June 2019, Savannah,IFASD Georgia,-2019- USA106 THEODORSEN’S AND GARRICK’S COMPUTATIONAL AEROELASTICITY, REVISITED Boyd Perry, III NASA – Langley Research Center Hampton, Virginia 23681-2199 USA [email protected] Keywords: Flutter; NACA Reports 496, 685, 741; Theodore Theodorsen; I.E. Garrick Abstract: This paper describes a multiyear effort to recompute all of the numerical flutter results contained in Theodore Theodorsen’s and I.E. Garrick’s (“T&G’s”) groundbreaking trilogy of National Advisory Committee for Aeronautics technical reports on aeroelastic flutter (NACA Reports 496, 685, and 741). The paper includes overviews of T&G’s aeroelastic equations and solution methods, comparisons between the original and recomputed numerical results, and instances of errors and tripping points (potentials for confusing the reader) in the original NACA reports. 1 INTRODUCTION In 1934, starting from first principles, Theodore Theodorsen laid out the theory of aeroelastic flutter for a typical section with three degrees of freedom and provided a method for its practical solution [1]. At the time, this solution method offered the only means of solving the flutter problem in an exact closed-form way. To borrow today’s terminology and retroactively apply it to 1934, it can be argued that reference 1 was the original paper on computational aeroelasticity, the only differences between the original and today’s variations being the accuracy and fidelity of their respective structural and unsteady aerodynamic representations. There were follow-on papers in 1938 [2] and 1942 [3] co-authored with I.E.
    [Show full text]
  • Plasma Aerodynamics Since the End of the Cold War Dennis C
    Florida State University Libraries Electronic Theses, Treatises and Dissertations The Graduate School 2012 Plasma Aerodynamics since the End of the Cold War Dennis C. Mills Follow this and additional works at the FSU Digital Library. For more information, please contact [email protected] THE FLORIDA STATE UNIVERSITY COLLEGE OF ARTS AND SCIENCES PLASMA AERODYNAMICS SINCE THE END OF THE COLD WAR By DENNIS C. MILLS A Dissertation submitted to the Department of History in partial fulfillment of the requirements for the degree of Doctor of Philosophy Degree Awarded: Summer Semester, 2012 Dennis C. Mills defended this dissertation on April 19, 2012. The members of the supervisory committee were: Jonathan Grant Professor Directing Dissertation Michael Ruse University Representative Frederick Davis Committee Member Edward Wynot Committee Member Rafe Blaufarb Committee Member The Graduate School has verified and approved the above-named committee members, and certifies that the dissertation has been approved in accordance with university requirements. ii To my mother and my wife. iii ACKNOWLEDGEMENTS This journey began back in junior high school around 1970 when I first realized I enjoyed history. Many people helped along the way and I truly wish I could personally thank each and every one of them for the achievement of a life-long dream. They assisted in this long journey and I am forever in their gratitude. iv TABLE OF CONTENTS ABSTRACT ..................................................................................................................................
    [Show full text]
  • Commencement 1920-1940
    THE JOHNS HOPKINS UNIVERSITY BALTIMORE Conferring of Degrees At The Close Of The Fifty-Third Academic Year JUNE 11, 1929 IN THE LYRIC THEATRE AT 4 P- M. MARSHALS Professor William 0. Wetforth Chief Marshal Aids Professor G. H. Cabtledge Professor Florence E. Bamberger Dr. E. T. Abercrombie Professor A. M. Chesney Dr. G. H. Evans Professor W. W. Ford Professor J. C. Smallwood Professor S. J. Hart USHERS William Purnell Hall, Jr. Chief Usher George Gump Maxwell Sauerwein George Kay Walter Scheidt Burrell Kilmer Fred Waring Edwin Lockard S. Carson Wasson Robert Lyons MUSIC The program is under the direction of Philip S. Morgan and will be presented by the Johns Hopkins Orchestra, Bail Wirtz, Conductor. The orchestra was founded in 1919 by the Johns Hopkins Musical Association, organized for the promotion of good music in the University and community, the officers of which are Philip S. Morgan, of the Johns Hopkins Alumni Association, President; Frederick H. Gottlieb, Vice-Presi- dent; Professor Frank Morley, Secretary; Ferdinand C. Smith, Executive Secretary; S. Page Nelson, Treasurer. Seventy-three symphony concerts have been given, and the orchestra, which is composed chiefly of amateurs, has played on nineteen occasions for public exercises of the University. — —— ORDER OF EXERCISES i Academic Procession War March from " Athalie " Mendelssohn II Invocation The Reverend Charles E. McAllister Rector of St. Michaels and All Angels Church in Address Dr. Frederick George Donnan Professor of General Chemistry, University College, London IV
    [Show full text]
  • Scientific American, July, 1956
    SCIENTIFIC ERIC ANTIOCHUS I, KING OF KOMMAGENE F/FTYCENTS �/956 © 1956 SCIENTIFIC AMERICAN, INC A pound of fuel to light Chicago THAT'S ALL THE URANIUM needed to produce atomic production processes, to test product quality, and for power equal to the energy in 3 million pounds of coal. research. It could light Chicago for a full day! THE CHALLENGING FIELD of atomic energy is not ATOMIC RESEARCH is focused on developing an eco­ new to the people of Union Carbide. They have been nomical way to produce electricity from atomic energy. pioneering in every phase of this exciting business­ Scientists at Oak Ridge National Laboratory, which from the mining of uranium ore to harnessing the atom Union Carbide Nuclear Company operates for the for ·our future comfort and well-being. Atomic Energy Commission, have already built experi­ F R E E: To learn more about the atom and the tremendous mental power producing reactors that are serving as a strides made in the peaceJul applications oj atomic energy, guide to commercial atom power plants. write Jor the illustrated booklet "The Atom In Our Hands." PEACEFUL USES for the atom have also been found in the diagnosis and treatment of disease. Radioactivity is UNION CARBIDE uncovering important facts about plant and animal AND CARBON CORPORATION growth. Industry uses the atom's radiation to control 30 EAST 42ND STREET 00 NEW YORK 17. N. Y. In Canada: UNION CARBIDE CANADA LIMITED, Toronto VCC's Trade-marked Products include ELECTROMET Alloys and Metals CRAG Agricultural Chemicals NATIONAL Carbons ACHESON
    [Show full text]
  • NASA-TP-2020-220562 Replacement.Pdf
    NASA/TP–2020-220562 Re-Computation of Numerical Results Contained in NACA Report No. 685 Boyd Perry, III Langley Research Center, Hampton, Virginia J February 2020 NASA STI Program . in Profile Since its founding, NASA has been dedicated to the • CONFERENCE PUBLICATION. advancement of aeronautics and space science. The Collected papers from scientific and technical NASA scientific and technical information (STI) conferences, symposia, seminars, or other program plays a key part in helping NASA maintain meetings sponsored or this important role. co-sponsored by NASA. The NASA STI program operates under the auspices • SPECIAL PUBLICATION. Scientific, of the Agency Chief Information Officer. It collects, technical, or historical information from NASA organizes, provides for archiving, and disseminates programs, projects, and missions, often NASA’s STI. The NASA STI program provides access concerned with subjects having substantial to the NTRS Registered and its public interface, the public interest. NASA Technical Reports Server, thus providing one of the largest collections of aeronautical and space • TECHNICAL TRANSLATION. science STI in the world. Results are published in both English-language translations of foreign non-NASA channels and by NASA in the NASA STI scientific and technical material pertinent to Report Series, which includes the following report NASA’s mission. types: Specialized services also include organizing • TECHNICAL PUBLICATION. Reports of and publishing research results, distributing completed research or a major significant phase of specialized research announcements and feeds, research that present the results of NASA providing information desk and personal search Programs and include extensive data or theoretical support, and enabling data exchange services. analysis. Includes compilations of significant scientific and technical data and information For more information about the NASA STI program, deemed to be of continuing reference value.
    [Show full text]
  • Computational Fluid Dynamics Simulations of Oscillating Wings and Comparison to Lifting-Line Theory
    Utah State University DigitalCommons@USU All Graduate Theses and Dissertations Graduate Studies 5-2015 Computational Fluid Dynamics Simulations of Oscillating Wings and Comparison to Lifting-Line Theory Megan Keddington Utah State University Follow this and additional works at: https://digitalcommons.usu.edu/etd Part of the Aerospace Engineering Commons Recommended Citation Keddington, Megan, "Computational Fluid Dynamics Simulations of Oscillating Wings and Comparison to Lifting-Line Theory" (2015). All Graduate Theses and Dissertations. 4473. https://digitalcommons.usu.edu/etd/4473 This Thesis is brought to you for free and open access by the Graduate Studies at DigitalCommons@USU. It has been accepted for inclusion in All Graduate Theses and Dissertations by an authorized administrator of DigitalCommons@USU. For more information, please contact [email protected]. COMPUTATIONAL FLUID DYNAMICS SIMULATIONS OF OSCILLATING WINGS AND COMPARISON TO LIFTING-LINE THEORY by Megan Keddington A thesis submitted in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE in Aerospace Engineering Approved: ____________________ ____________________ Warren F. Phillips Steven L. Folkman Major Professor Committee Member ____________________ ____________________ Douglas F. Hunsaker Mark R. McLellan Committee Member Vice President for Research and Dean of the School of Graduate Studies UTAH STATE UNIVERSITY Logan, Utah 2015 ii Copyright © Megan Keddington 2015 All Rights Reserved iii ABSTRACT Computational Fluid Dynamics Simulations of Oscillating Wings and Comparison to Lifting-Line Solution by Megan Keddington Utah State University, 2015 Major Professor: Dr. Warren F. Phillips Department: Mechanical and Aerospace Engineering Computational fluid dynamics (CFD) analysis was performed in order to compare the solutions of oscillating wings with Prandtl’s lifting-line theory.
    [Show full text]