ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • Other Sources  (855)
  • 1935-1939  (855)
Collection
Source
Keywords
Publisher
Language
Years
Year
  • 1
    facet.materialart.
    Unknown
    New evidence for a change in physical conditions at depths near 100 kilometers (1939)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 29, no. 6, pp. 531-538, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Physical properties of rocks ; BSSA
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 2
    facet.materialart.
    Unknown
    Tsunamis and earthquakes (1939)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 29, no. 6, pp. 517-526, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; BSSA
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 3
    facet.materialart.
    Unknown
    Zur Entwicklung der seismographischen Aufschlußmethoden (1939)
    In:  Ergebnisse der kosmischen Physik, Milano, Gustav Fischer, vol. 4, no. 6, pp. 169-218, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Applied geophysics ; Seismics (controlled source seismology)
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 4
    facet.materialart.
    Unknown
    The velocity of sound waves and the temperature in the stratosphere in Southern California (1939)
    In:  Bull. Am. Meteor. Soc., Milano, Gustav Fischer, vol. 20, no. 6, pp. 192-201, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Velocity analysis ; Geothermics ; Meteorology ; Acoustics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 5
    facet.materialart.
    Unknown
    Correspondence and discussion on Chile earthquake of November 10, 1922 (1939)
    In:  Earthquake Notes, Milano, Gustav Fischer, vol. 10,No. 4, no. 6, pp. 9-10, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Seismology ; Earthquake
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 6
    facet.materialart.
    Unknown
    New evidence for a change in physical conditions at depths near 100 kilometers (1939)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 50, no. 6, pp. 1950, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Physical properties of rocks
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 7
    facet.materialart.
    Unknown
    Observations with electromagnetic microbarographs (1939)
    In:  Nature, Beijing, Pergamon, vol. 144, no. 3-4, pp. 478-479, pp. 1246
    Details
    Publication Date: 1939
    Keywords: Instruments ; Electromagnetic methods/phenomena ; Meteorology
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 8
    facet.materialart.
    Unknown
    Waves and currents recorded by electromagnetic barographs (1939)
    In:  Bull. Am. Meteor. Soc., Beijing, Pergamon, vol. 20, no. 3-4, pp. 421-426, pp. 1246
    Details
    Publication Date: 1939
    Keywords: Waves ; Electromagnetic methods/phenomena ; Instruments ; Meteorology
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 9
    facet.materialart.
    Unknown
    The structure of the Pacific basin as indicated by earthquakes (1939)
    In:  Science, Milano, Gustav Fischer, vol. 90, no. 6, pp. 456-458, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; Earth model, also for more shallow analyses !
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 10
    facet.materialart.
    Unknown
    Depth and geographical distribution of deep-focus earthquakes II (1939)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 50, no. 6, pp. 1511-1528, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; Hypocentral depth
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 11
    facet.materialart.
    Unknown
    On seismic waves (fourth paper) (1939)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 54, no. 6, pp. 94-136, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1939
    Keywords: Waves ; Seismology ; Review article
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 12
    facet.materialart.
    Unknown
    The Alaskan earthquake of July 22, 1937 (1939)
    In:  Bull. Seism. Soc. Am., Dordrecht, D. Reidel, vol. 30, no. 1, pp. 353-376
    Details
    Publication Date: 1939
    Keywords: Seismology ; Earthquake ; Source ; BSSA
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 13
    facet.materialart.
    Unknown
    The Mammoth "Earthquake Fault" and the related features in Mono County, California (1939)
    In:  Bull. Seism. Soc. Am., Beijing, Pergamon, vol. 29, no. 3-4, pp. 333-340, pp. 1246
    Details
    Publication Date: 1939
    Keywords: Seismology ; Seismicity ; Fault zone ; Geol. aspects ; Tectonics ; BSSA
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 14
    facet.materialart.
    Unknown
    Some considerations on the fields of stresses connected with dislocations in a regular crystal lattice (1939)
    In:  Proc. Koninkl. Ned. Akad. Wetenschap., Hannover, FU Berlin, vol. 42, no. 3, pp. 293, pp. 5091692, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1939
    Keywords: Stress ; Dislocation ; Rock mechanics ; Elasticity
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 15
    facet.materialart.
    Unknown
    Evidence from deep-focus earthquakes (1939)
    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. XI:, pp. 291-299, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Seismology ; Hypocentral depth
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 16
    facet.materialart.
    Unknown
    Control of the may-beetle in protectove strips of forest trees [Melolontha hippocastani] (1939)
    In:  Soc. Grain Farmg., Saratoff, Nr. 3, p.132-136
    Details
    Publication Date: 1939
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 17
    facet.materialart.
    Unknown
    Groß-Schneefälle in Deutschland, insbesondere die Schneebruchkatastrophe vom 16. April 1936 (1939)
    In:  Meteorol. Ztschr. 56: 418-428
    Details
    Publication Date: 1939
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 18
    facet.materialart.
    Unknown
    High temperature tolerance of forest trees (1939)
    In:  Minnesota agric. Exp. Stat. Techn. Bull. 141: 25pp
    Details
    Publication Date: 1939
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 19
    facet.materialart.
    Unknown
    Die Frühjahrsfröste an der Unterelbe und ihre Bekämpfung (1939)
    In:  Zeitschr. angew. Meterologie. 56. Jahrgang. Heft 9. S.273-289
    Details
    Publication Date: 1939
    Description: Bericht über die Entwicklung von Spätfrösten im norddeutschen Flachland, über die Frühwarnung und über Untersuchungen zur Brauchbarkeit von Frostschutzversuchen KATASTER-BESCHREIBUNG: Einfluss der Temperatur auf den Ertrag KATASTER-DETAIL: Delta T (März) + und Delta T (April) - (Frost), dann Schäden an Obstbäumen + und Ertrag -;
    Keywords: Norddeutschland, Unterelbe ; 1930-1939 ; Boden ; Ertrag ; Temperatur ; Wind ; Witterung ; Globalstrahlung ; Frost ; Obst
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 20
    facet.materialart.
    Unknown
    Das Massenauftreten von pflanzenschädigenden Insekten (1939)
    In:  In: R.Otto u.a., Organismen und Umwelt (Th.Steinkopff, Dresden u. Leipzig); p.182-196
    Details
    Publication Date: 1939
    Description: Erkenntnisse aus Laborversuchen über die Zusammenhänge zwischen Temperatur, sowie Feuchte und dem Auftreten von Forleule, Traubenwickler, Kieferneule, Kartoffelkäfer und Nonne werden diskutiert. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Forst ; Pflanzenschädling ; Hackfrüchte ; Wein
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 21
    facet.materialart.
    Unknown
    Reflexion et Refraction des Ondes Seismiques Progressives (1939)
    Gauthier-Villars
    In:  Paris, Gauthier-Villars, vol. 3, no. 3, pp. 275-291, (ISBN 0-415-24328-9 (hb), 0-203-47128-8 (pb))
    Details
    Publication Date: 1939
    Keywords: Waves ; Refraction seismics ; Reflection seismics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 22
    facet.materialart.
    Unknown
    Internal Constitution of the Earth - Physic of the Earth 1st ed. (1939)
    McGraw-Hill
    In:  New York, 10 + 413 pp.,, McGraw-Hill, vol. 7, no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Handbook of geophysics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 23
    facet.materialart.
    Unknown
    Introduction (1939)
    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. I:, pp. 3-10, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Review article
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 24
    facet.materialart.
    Unknown
    The cooling of the earth and the temperature in its interior (1939)
    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. VII:, pp. 153-164, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Geothermics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 25
    facet.materialart.
    Unknown
    Structure of the crust (1939)
    McGraw-Hill
    In:  New York, 10 + 413 pp., 1st ed., McGraw-Hill, vol. 7, no. XII:, pp. 301-327, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: CRUST ; Earth model, also for more shallow analyses !
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 26
    facet.materialart.
    Unknown
    Summary (1939)
    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Review article
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 27
    facet.materialart.
    Unknown
    Forces in the earth's crust (1939)
    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. VIII:, pp. 165-175, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; CRUST ; Crustal deformation (cf. Earthquake precursor: deformation or strain)
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 28
    facet.materialart.
    Unknown
    Hypotheses on the development of the earth's crust and their implications (1939)
    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. IX:, pp. 177-217, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; CRUST
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 29
    facet.materialart.
    Unknown
    The elastic constants in the interior of the earth (1939)
    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. XIV:, pp. 345-360, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Elasticity
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 30
    facet.materialart.
    Unknown
    Viscosity, strength, and internal friction in the interior of the earth (1939)
    McGraw-Hill
    In:  New York, McGraw-Hill, vol. 7, no. XV:, pp. 361-384, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1939
    Keywords: Earth model, also for more shallow analyses ! ; Stress ; Strength ; Elasticity ; Inelastic
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 31
    facet.materialart.
    Unknown
    Tests in the Gust Tunnel of a Model of the XBM-1 Airplane (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-731
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 32
    facet.materialart.
    Unknown
    An Instrument for Estimating Tautness of Doped Fabrics on Aircraft (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-729
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 33
    facet.materialart.
    Unknown
    Calculation of the induced efficiency of heavily loaded propellers having infinite number of blades (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-884
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 34
    facet.materialart.
    Unknown
    Comparison of theory with experiment in the phenomenon of wing flutter (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Direct measurements were undertaken at the Aeronautics Laboratory in Turin of the aerodynamic actions on an oscillating wing. The tests conducted had as their essential object the examination of the operation of apparatus designed for this measurement. The values experimentally obtained for the aerodynamic coefficients are in good agreement with the theory of oscillatory motion of the wing of finite span and show clear deviation from the values obtained by theory of plane motion.
    Type: NACA-TM-887
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 35
    facet.materialart.
    Unknown
    Investigation of the lift distribution over the separate wings of a biplane (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation is made of the mutual interference of the wings of a biplane under the general assumption that each wing may be replaced by a vortex system of the type given by the Prandtl wing theory. The additional velocities induced at each wing by the presence of the other are determined by the Biot-Savart law and converted into an equivalent change in the angle of attack, the effect being that of an additional twist given to the wings in changing their lift distributions. The lift distributions computed in this manner for several airplane types are compared with the results of measurement.
    Type: NACA-TM-889
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 36
    facet.materialart.
    Unknown
    The Way to Increased Airplane Engine Power (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this paper is to give an outline of the present state of development and point out the possibilities available for the further increase in the power/displacement ratio, the economy, and the reliability of the engine. Some of the aspects discussed are methods of increasing take-off power, the various methods of preparation of the fuel mixture and their effect on power, economy, and safety.
    Type: NACA-TM-894
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 37
    facet.materialart.
    Unknown
    The limit of stability of a curved plate strip under shear and axial stresses (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For an infinitely long plate strip of constant curvature there is set up the buckling condition for combined shear and axial stresses. Assumptions are made of the vanishing of the moments acting on the longitudinal edges and of the vanishing of the tangential displacements u and the transverse stresses sigma(sub y) (longitudinal stiffeners nonresistant to bending in the circumferential direction). The buckling condition is evaluated for the case of pure shear and an approximate formula is derived for the critical stresses for large curvatures. In connection with the discussion of the methods and results there is defined the range of validity and the buckling condition set up.
    Type: NACA-TM-898
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 38
    facet.materialart.
    Unknown
    Design of centrifugal impeller blades (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper restricts itself to radial impellers with cylindrical blades since, as Prasil has shown, the flow about an arbitrarily curved surface of revolution may be reduced to this normal form we have chosen by a relatively simple conformal transformation. This method starts from the simple hypotheses of the older centrifugal impeller theory by first assuming an impeller with an infinite number of blades. How the flow is then modified is then investigated. For the computation of flow for a finite number of blades, the approximation method as developed by Munk, Prandtl and Birnbaum, or Glauert is found suitable. The essential idea of this method is to replace the wing by a vortex sheet and compute the flow as the field of these vortices. The shape of the blades is then obtained from the condition that the flow must be along the surface of the blade.
    Type: NACA-TM-902
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 39
    facet.materialart.
    Unknown
    Effect of transition in cross-sectional shape on the development of the velocity and pressure distribution of turbulent flow in pipes (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: With regard to the change in shape of the cross section while the area remains constant, no investigation results are as yet available. Such an investigation will be the subject of the present paper. For this purpose it is necessary to consider the velocity and pressure relations over each entire cross section so that we are confronted with a three-dimensional problem.
    Type: NACA-TM-903
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 40
    facet.materialart.
    Unknown
    The Enlarged N.A.C.A. Tank, and Some of Its Work (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The most conspicuous of the features of the enlarged N.A.C.A. tank are derived directly from those of the original tank and owe their present form not only to the reasons for their first use but also to the experience obtained with them. As in the original tank, there are: 1) A basin of great length (new 2,880 feet); 2) Rails made of structural H beams, without machining; 3) A towing carriage of very high speed (now 80 mph maximum); 4) Rubber tires on all the wheels, pneumatic on the running wheels and solid on the guide wheels.
    Type: NACA-TM-918
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 41
    facet.materialart.
    Unknown
    Ice Formation on Wings (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report makes use of the results obtained in the Gottingen ice tunnel in which the atmospheric conditions are simulated and the process of ice formation photographed. The effect of ice formation is threefold: 1) added weight to the airplane; 2) a change in the lift and drag forces; 3) a change in the stability characteristics.
    Type: NACA-TM-888 , Lilienthal-Gesellschaft fur Luftfahrtforschung ( 1938 : Berlin)
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 42
    facet.materialart.
    Unknown
    The Power of Aircraft Engines at Altitude (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The subject of the present paper is confined to the investigations and methods employed by the Fiat company in their studies on the altitude performance of an air-cooled engine of the production type. The experimental set-up as well as test engine data are provided.
    Type: NACA-TM-895 , Lilienthal-Gesellschaft fur Luftfahrtforschung ( 1938 : Berlin)
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 43
    facet.materialart.
    Unknown
    The hydrodynamic theory of detonation (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report derives equations containing only directly measurable constants for the quantities involved in the hydrodynamic theory of detonation. The stable detonation speed, D, is revealed as having the lowest possible value in the case of positive material velocity, by finding the minimum of the Du curve (u denotes the speed of the gases of combustion). A study of the conditions of energy and impulse in freely suspended detonating systems leads to the disclosure of a rarefaction front traveling at a lower speed behind the detonation front; its velocity is computed. The latent energy of the explosive passes into the steadily growing detonation zone - the region between the detonation front and the rarefaction front. The conclusions lead to a new definition of the concept of shattering power. The calculations are based on the behavior of trinitrotoluene.
    Type: NACA-TM-899
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 44
    facet.materialart.
    Unknown
    Stability of rectangular plates with longitudinal or transverse stiffeners under uniform compression (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the present paper, the complete buckling conditions of stiffened plates are being developed for uniform compression. We shall treat plates with one or two longitudinal or transverse stiffeners at any point, discuss the buckling conditions, and evaluate them for different cases.
    Type: NACA-TM-904
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 45
    facet.materialart.
    Unknown
    Two-stroke-cycle engines with unsymmetrical control diagram : supercharged engines (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As no investigation of supercharging in 2-stroke-cycle engines has been published up to the present, this article is an attempt in that direction, with a view to establishing the mathematical principles and the constructive rules for the design of such engines.
    Type: NACA-TM-908
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 46
    facet.materialart.
    Unknown
    Measurement of the True Dynamic and Static Pressures in Flight (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this report, two reliable methods are presented, with the aid of which the undisturbed flight dynamic pressure and the true static pressure may be determined without error. These problems were solved chiefly through practical flight tests.
    Type: NACA-TM-913
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 47
    facet.materialart.
    Unknown
    Theory of two-dimensional potential flow about arbitrary wing sections (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Three general theories treating the potential flow about an arbitrary wing section are discussed in this report. The first theory treats the method of conformal transformation as laid down by Theodorsen and Garrick; the second is a generalization of Birnbaum's theory for moderately thick airfoils; the third is a general investigation of the complex velocity function with particular reference to the relations first discussed by F. Weinig.
    Type: NACA-TM-886
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 48
    facet.materialart.
    Unknown
    Experiments on a Slotted Wing (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of pressure distribution measurements that were made on a model wing section of a Fieseler F 5 R type airplane are presented. Comparison of those model tests with the corresponding flight tests indicates the limitations and also the advantages of wind tunnel investigations, the advantages being particularly that through the variety of measuring methods employed the more complicated flow conditions may also be clarified. A fact brought out in these tests is that even in the case of "well rounded" slots it is possible for a vortex to be set up at the slot entrance and this vortex is responsible for certain irregularities in the pressure distribution and in the efficiency of the slot.
    Type: NACA-TM-890
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 49
    facet.materialart.
    Unknown
    Contribution to the theory of the heated duct radiator (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method is developed with no neglect of certain factors in mass flow of air and in the drag of the heated radiator, i.e., one under actual operating conditions, as compared with the corresponding values in the cold state, may be simply computed. Although a symmetrical duct radiator has been used to bring out the flow relations, the results apply equally as well to the unsymmetrical radiator shapes usual in airplane construction.
    Type: NACA-TM-893
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 50
    facet.materialart.
    Unknown
    Airfoil Theory at Supersonic Speed (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl airfoil theory of 1918-1919 for incompressible flow. In addition to the profile and induced drags, account must be taken at supersonic flow of still another drag, namely, the wave drag, which is independent of the wing aspect ratio. Both wave and induced drags are proportional to the square of the lift and depend on the Mach number, that is, the ratio of flight to sound speed. In general, in the case of supersonic flow, the drag-lift ratio is considerably less favorable than is the case for incompressible flow. Among others the following examples are considered: 1) lifting line with constant lift distribution (horseshoe vortex); 2) computation of wave and induced drag and the twist of a trapezoidal wing of constant lift density; 3) computation of the lift distribution and drag of an untwisted rectangular wing.
    Type: NACA-TM-897
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 51
    facet.materialart.
    Unknown
    The effect of the masses of the controls on the longitudinal stability with free elevator. Part I (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the present report, aerodynamic relations under the effect of the weight moments are investigated, and an example given of the computation of the stability for a practical case. Later, the effects of the masses of the controls on the dynamic longitudinal stability will be considered.
    Type: NACA-TM-900
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 52
    facet.materialart.
    Unknown
    Temperature-indicating Paints (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is an attempt at a new method of coating the surface of the cylinder with materials that undergo chemical change at definite temperatures as indicated by a change in color. In this way it was hoped that the substance itself would indicate directly the position of its isotherms, which in measurements with thermocouples requires a tedious amount of labor.
    Type: NACA-TM-905
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 53
    facet.materialart.
    Unknown
    Ground-cooling and Flight Tests of an Airplane Equipped with a Nose-blower Engine Cowling (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-478
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 54
    facet.materialart.
    Unknown
    Preliminary report on the characteristics of the NACA 4400R series airfoils (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-451
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 55
    facet.materialart.
    Unknown
    Preliminary Report on Laminar-Flow Airfoils and New Methods Adopted for Airfoil and Boundary-Layer Investigations (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recent developments in airfoil-testing methods and fundamental air-flow investigations, as applied to airfoils, are discussed. Preliminary test results, obtained under conditions relatively free from stream turbulence and other disturbances, are presented. Suitable airfoils and airfoil-design principles were developed to take advantage of the unusually extensive laminar boundary layers that may be maintained under the improved testing conditions. The results are of interest mainly in range of below 6,000,000.
    Keywords: Aerodynamics
    Type: NACA-WR-L-345
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 56
    facet.materialart.
    Unknown
    Acceleration, Stress, and Deflection Measurements on the XB-15 Bomber in Gusty Air (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-540
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 57
    facet.materialart.
    Unknown
    The Effect of Nacelle-Propeller Diameter Ratio on Body Interference and on Propeller and Cooling Characteristics (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of an investigation conducted in the NACA 20-foot tunnel to determine the slipstream drag, the body interference, and the cooling characteristics of nacelle-propeller diameter. Four combinations of geometrically similar propellers and nacelles, mounted on standard wing supports, were tested with values of the ratio of nacelle diameter to propeller diameter of 0.25, 0.33, and 0.44.
    Type: NACA-TR-680
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 58
    facet.materialart.
    Unknown
    Surface heat-transfer coefficients of finned cylinders (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation to determine and correlate the experimental surface heat-transfer coefficients of finned cylinders with different air-stream cooling arrangements was conducted at the Langley Memorial Aeronautical Laboratory from 1932 to 1938. The investigation covered the determination of the effect of fin width, fin space, fin thickness, and cylinder diameter on the heat transfer. Wind-tunnel tests were made in the free air stream with and without baffles and also with various devices for creating a turbulent air stream. Tests were also made with blower.
    Type: NACA-TR-676
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 59
    facet.materialart.
    Unknown
    Effects of Elevator Nose Shape, Gap, Balance, and Tabs on the Aerodynamic Characteristics of a Horizontal Tail Surface (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are presented showing the effects of gap, elevator, nose shape, balance, cut-out, and tabs on the aerodynamic characteristics of a horizontal tail surface tested in the NACA full-scale tunnel.
    Type: NACA-TR-675
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 60
    facet.materialart.
    Unknown
    Determination of the Profile Drag of an Airplane Wing in Flight at High Reynolds Numbers (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight tests were made to determine the profile-drag coefficients of a portion of the original wing surface of an all-metal airplane and of a portion of the wing made aerodynamically smooth and more nearly fair than the original section. The wing section was approximately the NACA 2414.5. The tests were carried out over a range of airplane speeds giving a maximum Reynolds number of 15,000,000. Tests were also carried out to locate the point of transition from laminar to turbulent boundary layer and to determine the velocity distribution along the upper surface of the wing. The profile-drag coefficients of the original and of the smooth wing portions at a Reynolds number of 15,000,000 were 0.0102 and 0.0068, respectively; i.e., the surface irregularities on the original wing increased the profile-drag coefficient 50 percent above that of the smooth wing.
    Type: NACA-TR-667
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 61
    facet.materialart.
    Unknown
    Interference of Tail Surfaces and Wing and Fuselage from Tests of 17 Combinations in the N.A.C.A. Variable-Density Tunnel (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the interference associated with tail surfaces added to wing-fuselage combinations was included in the interference program in progress in the NACA variable-density tunnel. The results indicate that, in aerodynamically clean combinations, the increment of the high-speed drag can be estimated from section characteristics within useful limits of accuracy. The interference appears mainly as effects on the downwash angle and as losses in the tail effectiveness and varies with the geometry of the combination. An interference burble, which markedly increases the glide-path angle and the stability in pitch before the actual stall, may be considered a means of obtaining satisfactory stalling characteristics for complete combination.
    Type: NACA-TR-678
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 62
    facet.materialart.
    Unknown
    Wind-tunnel investigation of NACA 23012 airfoil with various arrangements of slotted flaps (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made in the NACA 7 by 10-foot wind tunnel of a large-chord NACA 23012 airfoil with several arrangements of 25.66 percent chord slotted flaps to determine the section aerodynamic characteristics as affected by slot shape, flap shape, flap location, and flap deflection. The flap position for maximum lift, the polars for arrangements considered favorable for take-off and climb, and the complete section aerodynamic characteristics for selected optimum arrangements were determined. A discussion is given of the relative merits of the various arrangement for certain selected criterions. A comparison is made of a slotted flap on the NACA 23021 airfoil with a corresponding slotted flap previously developed for the NACA 23012 airfoil.
    Type: NACA-TR-677
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 63
    facet.materialart.
    Unknown
    Cooling on the Front of an Air-cooled Engine Cylinder in a Conventional Engine Cowling (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements were made of the cooling on the fronts of model cylinders in a conventional cowling for cooling in both the ground and the cruising conditions. The mechanisms of front and rear cooling are essentially different. Cooling on the rear baffled part of the cylinders continually increases with increasing fin width. For the front of the cylinder, an optimum fin width was found to exist beyond which an increase in width reduced the heat transfer. The heat transfer coefficient on the front of the cylinders was larger on the side of the cylinder facing the propeller swirl than on the opposite side. This effect became more pronounced as the fin width was increased. These results are introductory to the study of front cooling and show the general effect of several test parameters.
    Type: NACA-TR-674
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 64
    facet.materialart.
    Unknown
    Experimental Verification of the Theory of Oscillating Airfoils (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements have been made of the lift on an airfoil in pitching oscillation with a continuous-recording, instantaneous-force balance. The experimental values for the phase difference between the angle of attack and the lift are shown to be in close agreement with theory.
    Type: NACA-TR-673
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 65
    facet.materialart.
    Unknown
    Free-Spinning Wind-Tunnel Tests of a Low-Wing Monoplane with Systematic Changes in Wings and Tails IV : Effect of Center-of-Gravity Location (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Eight wings and three tails, covering a wide range of aerodynamic characteristics, were independently ballasted so as to be interchangeable with no change in mass distribution. For each of the 24 resulting wing-tail combinations, observations were made of the steady spin for four control settings and of recoveries for five control manipulations. The results are presented in the form of charts comparing the spin characteristics. The tests are part of a general investigation being made in the NACA free-spinning tunnel to determine the effects of systematic changes in wing and tail arrangement upon the steady-spin and the recovery characteristics of a conventional low-wing monoplane for various load distributions.
    Type: NACA-TR-672
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 66
    facet.materialart.
    Unknown
    A theoretical study of the moment on a body in a compressible fluid (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The extension to a compressible fluid of Lagally's theorem on the moment on a body in an incompressible fluid and Poggi's method of treating the flow of compressible fluids are employed for the determination of the effect of compressibility on the moment of an arbitrary body. Only the case of the two-dimensional subsonic flow of an ideal compressible fluid is considered. As examples of the application of the general theory, two well-known systems of profiles are treated; namely the elliptic profile and the symmetrical Joukowski profiles with sharp trailing edges. The effect of compressibility on the position of the center of pressure is also discussed. Several numerical examples of both the elliptic and the Joukowski profiles are given.
    Type: NACA-TR-671
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 67
    facet.materialart.
    Unknown
    Calculation of the aerodynamic characteristics of tapered wings with partial-span flaps (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Factors derived from wing theory are presented. By means of these factors, the angle of zero lift, the lift-curve slope, the pitching moment, the aerodynamic-center position, and the induced drag of tapered wings with partial-span flaps may be calculated. The factors are given for wings of aspect ratios 6 and 10 , of taper ratios from 0.25 to 1.00, and with flaps of various length. An example is presented of the method of application of the factors. Fair agreement with experimental results is shown for two wings of different taper ratio having plain flaps of various spacing.
    Type: NACA-TR-665
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 68
    facet.materialart.
    Unknown
    Effect of Service Stress on Impact Resistance, X-ray Diffraction Patterns, and Microstructure of 25s Aluminum Alloy (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of a great number of tests made to determine the effect of service stresses on the impact resistance, the x-ray diffraction patterns, and the microstructure of 25s aluminum alloy. Many of the specimens were taken from actual propeller blades and others were cut from 13/16-inch rod furnished by the Aluminum Company of America.
    Type: NACA-TR-659
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 69
    facet.materialart.
    Unknown
    General airplane performance (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Equations have been developed for the analysis of the performance of the ideal airplane, leading to an approximate physical interpretation of the performance problem. The basic sea-level airplane parameters have been generalized to altitude parameters and a new parameter has been introduced and physically interpreted. The performance analysis for actual airplanes has been obtained in terms of the equivalent ideal airplane in order that the charts developed for use in practical calculations will for the most part apply to any type of engine-propeller combination and system of control, the only additional material required consisting of the actual engine and propeller curves for propulsion unit. Finally, a more exact method for the calculation of the climb characteristics for the constant-speed controllable propeller is presented in the appendix.
    Type: NACA-TR-654
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 70
    facet.materialart.
    Unknown
    A Study of Air Flow in an Engine Cylinder (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 4-stroke-cycle test engine was equipped with a glass cylinder and the air movements within it were studied while the engine was being motored. Different types of air flow were produced by using shrouded intake valves in various arrangements and by altering the shape of the intake-air passage in the cylinder head. The air movements were made visible by mixing feathers with the entering air, and high-speed motion pictures were taken of them so that the air currents might be studied in detail and their velocities measured. Motion pictures were also taken of gasoline sprays injected into the cylinder on the intake stroke. The photographs showed that: a wide variety of induced air movements could be created in the cylinder; the movements always persisted throughout the compression stroke; and the only type of movement that persisted until the end of the cycle was rotation about the cylinder axis.
    Type: NACA-TR-653
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 71
    facet.materialart.
    Unknown
    The Pack Method for Compressive Tests of Thin Specimens of Materials Used in Thin-Wall Structures (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The strength of modern lightweight thin-wall structures is generally limited by the strength of the compression members. An adequate design of these members requires a knowledge of the compressive stress-strain graph of the thin-wall material. The "pack" method was developed at the National Bureau of Standards with the support of the National Advisory Committee for Aeronautics to make possible a determination of compressive stress-strain graphs for such material. In the pack test an odd number of specimens are assembled into a relatively stable pack, like a "pack of cards." Additional lateral stability is obtained from lateral supports between the external sheet faces of the pack and outside reactions. The tests seems adequate for many problems in structural research.
    Type: NACA-TR-649
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 72
    facet.materialart.
    Unknown
    Tests of NACA 0009, 0012, and 0018 Airfoils in the Full-Scale Tunnel (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the NACA full-scale wind tunnel to determine the aerodynamic characteristics of the NACA 0009, 0012, and 0018 airfoils, with the ultimate purpose of providing data to be used as a basis for comparison with other wind-tunnel data, mainly in the study of scale and turbulence effects. Three symmetrical 6 by 36-foot rectangular airfoils were used. The Reynolds number range for minimum drag was form 1,800,000 to 7,000,000 and for maximum lift, from 1,700,000 to 4,500,000. The effect of rounded tips was determined for each of the airfoils. Tests were also made of the NACA 0012 airfoil equipped with a 0.20c full-span split flap hinged at 0.80c. Tuft surveys were included to show the progressive breakdown of flow near maximum lift. Momentum surveys were made in conjunction with force measurements at zero lift as an aid in converting force-test data to section coefficients.
    Type: NACA-TR-647
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 73
    facet.materialart.
    Unknown
    The Compressibility Burble and the Effect of Compressibility on Pressures and Forces Acting on a Airfoil (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Simultaneous air-flow photographs and pressure-distribution measurements were made of the NACA 4412 airfoil at high speeds to determine the physical nature of the compressibility burble. The tests were conducted in the NACA 24-inch high-speed wind tunnel. The flow photographs were obtained by the Schlieren method and the pressures were simultaneously measured for 54 stations in the 5-inch-chord airfoil by means of a multiple-tube manometer. Following the general program, a few measurements of total-pressure loss in the wake of the airfoil at high speeds were made to illustrate the magnitude of the losses involved and the extent of the disturbed region; and, finally, in order to relate this work to earlier force-test data, a force test of a 5-inch-chord NACA 4412 airfoil was made. The results show the general nature of the phenomenon known as the compressibility burble. The source of the increased drag is shown to be a compression shock that occurs on the airfoil as its speed approaches the speed of sound. Finally, it is indicated that considerable experimentation is needed in order to understand the phenomenon completely.
    Type: NACA-TR-646
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 74
    facet.materialart.
    Unknown
    A simple method of obtaining span load distributors (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-732
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 75
    facet.materialart.
    Unknown
    Wind-tunnel investigation of an N.A.C.A. 23021 airfoil with two arrangements of a 40-percent-chord slotted flap (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-728
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 76
    facet.materialart.
    Unknown
    Wind-tunnel investigation of effect of yawing on lateral-stability characteristics II : rectangular N.A.C.A. 23012 wing with a circular fuselage (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-730
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 77
    facet.materialart.
    Unknown
    A Flight Investigation of the Distribution of Ice-inhibiting Fluids on a Propeller Blade (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-727
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 78
    facet.materialart.
    Unknown
    Combined Beam-column Stresses of Aluminum-alloy Channel Sections (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of a research program to obtain design data on the strength of open-channel aluminum-alloy sections subjected to combined column and beam action. The results of the tests of about 70 specimens were graphed for stresses due to axial load and stresses due to bending loading as functions of length to radius of gyration of the specimens. From these graphs a design chart was derived that is suitable for ready use.
    Type: NACA-TN-726
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 79
    facet.materialart.
    Unknown
    Tests of an N.A.C.A. 23012 Airfoil with a slotted deflector flap (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Section aerodynamic characteristics of a large-chord N.A.C.A. 23012 airfoil with a slotted deflector flap were obtained in the N.A.C.A. 7- by 10-foot wind tunnel. The characteristics of an N.A.C.A. slotted flap and of a simple split flap are included for comparison. The slotted deflector flap was found to have a somewhat lower maximum lift coefficient and somewhat higher drag at high lift coefficients than the N.A.C.A. slotted flap. The high drag of the open slot with the deflector flap neutral indicates that the slot should be closed for this condition.
    Type: NACA-TN-699
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 80
    facet.materialart.
    Unknown
    Propeller Tests to Determine the Effect of Number of Blades at Two Typical Solidities (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Propellers with equal total blade area, but with different numbers, were tested at Stanford University. The tests show generally that, for equal total blade area, propellers with the larger number of blades absorb the greater power and, provided hubs have equal drag, develop the higher efficiency. It is shown that the differences found are in agreement, qualitatively, with what might be predicted from simple blade-element theory.
    Type: NACA-TN-698
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 81
    facet.materialart.
    Unknown
    The Frequency of Torsional Vibration of a Tapered Beam (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A solution for the equation of torsional vibration of tapered beams has been found in terms of Bessel functions for beams satisfying the following conditions: (a) the cross sections along the span are similar in shape; and (b) the torsional stiffness of a section can be expressed as a power of a linear function of distance along the span. The method of applying the analysis to actual cases has been described. Charts are given from which numerical values can be immediately obtained for most cases of practical importance. The theoretical values of the frequency ratio have been experimentally checked on five beams having different amounts of taper.
    Type: NACA-TN-697
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 82
    facet.materialart.
    Unknown
    Torsional Stability of Aluminum Alloy Seamless Tubing (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Torsion tests were made on 51ST aluminum-alloy seamless tubes having diameter-to-thickness ratios of from 77 to 139 and length-to-diameter ratios of from 1 to 60. The torsional strengths developed in the tubes which failed elastically (all tubes having lengths greater than 2 to 6 times the diameter) were in most cases within 10 percent of the value indicated by the theories of Donnel, Timoshenko, and Sturm, assuming a condition of simply supported ends.
    Type: NACA-TN-696
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 83
    facet.materialart.
    Unknown
    Tank Tests to Determine the Effects of the Chine Flare of a Flying-boat Hull N.A.C.A. Model Series 62 and 69 (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-725
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 84
    facet.materialart.
    Unknown
    The Effects of Some Surface Irregularities on Wing Drag (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The N.A.C.A. has conducted tests to provide more complete data than were previously available for estimating the effects of common surface irregularities on wing drag. The irregularities investigated included: brazier-head and countersunk rivets, spot welds, several types of sheet-metal joints, and surface roughness. Tests were also conducted to determine the over-all effect of manufacturing irregularities incidental to riveted aluminum alloy and to spot-welded stainless-steel construction. The tests were made in the 8-foot high speed wind tunnel at Reynolds Numbers up to 18,000,000. The results show that any of the surface irregularities investigated may increase wing drag enough to have important adverse effects on high-speed performance and economy. A method of estimating increases in wing drag caused by brazier-head rivets and lapped joints under conditions outside the range of the tests is suggested. Estimated drag increases due to rivets and lapped joints under conditions outside the range of the tests is suggested. Estimated drag increases due to rivets and lapped joints on a wing of 20-foot chord flying at 250 miles per hour are shown.
    Type: NACA-TN-695
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 85
    facet.materialart.
    Unknown
    Physical Properties of Synthetic Resin Materials (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made to determine the physical properties of synthetic resins having paper, canvas, and linen reinforcements, and of laminated wood impregnated with a resin varnish. The results show that commercial resins have moduli of elasticity that are too low for structural considerations. Nevertheless, there do exist plastics that have favorable mechanical properties and, with further development, it should be possible to produce resin products that compare favorably with the light-metal alloys. The results obtained from tests on Compound 1840, resin-impregnated wood, show that this material can stand on its own merit by virtue of a compressive strength four times that of the natural wood. This increase in compressive strength was accomplished with an increase of density to a value slightly below three times the normal value and corrected one of the most serious defects of the natural product.
    Type: NACA-TN-694
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 86
    facet.materialart.
    Unknown
    The Effects of Surface Waviness and of Rib Stitching on Wing Drag (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Surface waviness and rib stitching have been investigated as part of a series of tests to determine the effects on wing drag of common surface irregularities. The tests were made in the N.A.C.A. 8-foot high-speed wind tunnel at Reynolds Numbers up to 17,000,000. The results of the tests showed that the waviness common to airplane wings will cause no serious increase in drag unless the waviness exists on the forward part of the wing, where it may cause premature transition or premature compressibility effects. Waves 3 inches wide and 0.048 inch high, for example, increased the drag 1 percent when they covered the rear 67 percent of both surfaces and 10 percent when they covered the rear 92 percent. A single wave 3 inches wide and only 0.020 inch high at the 10.5-percent-chord point on the upper surface caused transition to occur on the wave and increased the drag 6 percent. Rib stitching increased the drag 7 percent when the rib spacing was 6 inches; the drag increment was proportional to the number of ribs for wider spacings. About one-third of the increase was due to premature transition at the forward ends of the stitching.
    Type: NACA-TN-724
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 87
    facet.materialart.
    Unknown
    Adhesion of Ice in Its Relation to the De-icing of Airplanes (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The various possible means of preventing ice adhesion on airplane surfaces are critically reviewed. Results are presented of tests of the adhesives forces between ice and various solid and liquid forces. It is concluded that the de-icing of airplane wings by heat from engine exhaust shows sufficient promise to warrant full-scale tests. For propellers, at least, and possibly for certain small areas such as windshields, radio masts, etc. the use of de-icing or adhesion-preventing liquids will provide the best means of protection.
    Type: NACA-TN-723
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 88
    facet.materialart.
    Unknown
    Comparison of Profile-drag and Boundary-layer Measurements Obtained in Flight and in the Full-scale Wind Tunnel (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of the existing turbulence in the full scale tunnel was determined from measurements of the profile drag of an N-22 section by the momentum method under corresponding conditions in flight and the tunnel. The transition-point location on the upper surface of the air-foil was also determined from velocity surveys in the boundary layer. The measurements were made at section lift coefficients from 0.480 to 0.635 with a range of Reynolds Numbers from 4,600,000 to 3,900,000. The results show that the end of transition occurs at approximately the same point on the airfoil in flight and in the tunnel. The transition region was somewhat broader in the tunnel and started farther forward than in flight. The laminar profiles in the tunnel had some characteristics of transition profiles in the tunnel and had a much steeper slope near the surface than did the laminar profiles obtained in flight. These differences, however, caused an increase of only 0.0001 in the profile-drag coefficients, as determined by the momentum method.
    Type: NACA-TN-693
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 89
    facet.materialart.
    Unknown
    Some fundamental considerations in regard to the use of power in landing an airplane (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is concerned with the effect of power on landing speed and apparent maximum lift coefficient. It is shown that when secondary effects are neglected, the maximum available increase in lift due to power is equal to the thrust being developed. If the increase in lift due to power is expressed in coefficient form, very high values may be shown under conditions which, on analysis, are found to be wholly impracticable in flight.
    Type: NACA-TN-692
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 90
    facet.materialart.
    Unknown
    Some elementary principles of shell stress analysis with notes on the use of the shear center (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The analysis of various types of shell under combined bending and torsion is discussed. The calculation and the use of the shear center are touched upon as incidental problems. Twelve fully worked numerical examples are given in an appendix.
    Type: NACA-TN-691
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 91
    facet.materialart.
    Unknown
    Resume of air-load data on slats and flaps (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A resume of the generally available test data regarding air loads on slats and flaps is presented and data attained up to the fall of 1938 are included. The data are given in the form of N.A.C.A. standard coefficients of air forces and moments on the lift-increasing device and, when available, the aerodynamic characteristics of the combined wing and high-lift device are included. Slats of the Handley Page type, fixed auxiliary airfoils, and flaps of several different types are covered.
    Type: NACA-TN-690
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 92
    facet.materialart.
    Unknown
    Local instability of centrally loaded columns of channel section and Z-section (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Charts are presented for the coefficients in formulas for the critical compressive stress at which cross-sectional distortion begins in a thin-wall member with either a channel section or a Z-section with identical flanges. The energy method of Timoshenko was used in the theoretical calculations required for the construction of the charts. The deflection equations were carefully selected to give good accuracy. The calculation of the critical compressive stress at stresses beyond the elastic range is briefly discussed. In order to demonstrate the use of the formulas and the charts in engineering calculations, two illustrative problems are included.
    Type: NACA-TN-722
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 93
    facet.materialart.
    Unknown
    Tandem Air Propellers (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests of 2-blade, adjustable-pitch, counter rotating tandem model propellers, adjusted to absorb equal power at maximum efficiency, were made at Stanford University. The characteristics, for 15 degrees, 25 degrees, 35 degrees, and 45 degrees pitch settings at 0.75 R of the forward propeller and for 8-1/2 percent, 15 percent, and 30 percent diameter spacings, were compared with those of 2-blade and 4-blade propellers of the same blade form. The tests showed that the efficiency of the tandem propellers was from 0.5 percent to 4 percent greater than that of a 4-blade propeller and, at the high blade-angle settings, not appreciably inferior to that of a 2-blade propeller. It was found that the rear tandem propeller should be set at a blade angle slightly less than that of the forward propeller to realize the condition of equal power at maximum efficiency. Under this condition the total power absorbed by the tandem propellers was from 3 percent to 9 percent more than that absorbed by the 4-blade propeller and about twice that absorbed by a 2-blade propeller.
    Type: NACA-TN-689
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 94
    facet.materialart.
    Unknown
    Compressive Tests of a Monocoque Box (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A monocoque box specimen of aluminum alloy was subjected to end compression and the strains in the stringers were measured up to loads at which permanent set became noticeable. The stringer strains at low loads agreed closely with those computed from the assumption of uniform stress distribution. Buckling of the 0.026-inch sheet between stringers and of the 0.075-inch shear web took place at stresses in accord with theoretical values. Permanent set became noticeable at a load of 115,200 pounds, corresponding to an average stringer stress of about 16,000 pounds per square inch. The measured average strain above the first buckling load was within 2 percent of the theoretical strain as calculated from the dimensions of the box and effective width formulas due to Marguerre and to Cox.
    Type: NACA-TN-721
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 95
    facet.materialart.
    Unknown
    Comparative Performance of Engines Using a Carburetor, Manifold Injection, and Cylinder Injection (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The comparative performance was determined of engines using three methods of mixing the fuel and the air: the use of a carburetor, manifold injection, and cylinder injection. The tests were made of a single-cylinder engine with a Wright 1820-G air-cooled cylinder. Each method of mixing the fuel and the air was investigated over a range of fuel-air ratios from 0.10 to the limit of stable operation and at engine speeds of 1,500 and 1,900 r.p.m. The comparative performance with a fuel-air ratio of 0.08 was investigated for speeds from 1,300 to 1,900 r.p.m. The results show that the power obtained with each method closely followed the volumetric efficiency; the power was therefore the highest with cylinder injection because this method had less manifold restriction. The values of minimum specific fuel consumption obtained with each method of mixing of fuel and air were the same. For the same engine and cooling conditions, the cylinder temperatures are the same regardless of the method used for mixing the fuel and the air.
    Type: NACA-TN-688
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 96
    facet.materialart.
    Unknown
    Loads imposed on intermediate frames of stiffened shells (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The loads imposed on intermediate frames by the curvature of the longitudinal and by the diagonal-tension effects are treated. A new empirical method is proposed for analyzing diagonal-tension effects. The basic formulas of the pure diagonal-tension theory are used, and the part of the total shear S carried by diagonal tension is assumed to be given the expression S (sub DT) = S (1-tau sub o/tau)(sup n) where tau (sub o) is the critical shear stress, tau the total (nominal shear stress), and n = 3 - sigma/tau where sigma is the stress in the intermediate frame. Numerical examples illustrate all cases treated.
    Type: NACA-TN-687
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 97
    facet.materialart.
    Unknown
    Local instability of columns with I-, Z-, channel, and rectangular-tube sections (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Charts are presented for the coefficients in the formulas for the critical compressive stress at which cross-sectional distortion begins in thin-wall columns of I-, Z-, channel, and rectangular-tube sections. The energy method of Timoshenko was used in the theoretical calculations required for the construction of the charts. The deflection equations were carefully selected to give good accuracy. The calculation of the critical compressive stress at stresses above the elastic range is briefly discussed in order to demonstrate the use of the formulas and the charts in engineering calculations. Two illustrative problems are included.
    Type: NACA-TN-743
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 98
    facet.materialart.
    Unknown
    Flight Tests of N.A.C.A. Nose-slot Cowlings on the BFC-1 Airplane (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of flight tests of four nose-slot cowling designs with several variations in each design are presented. The tests were made in the process of developing the nose-slot cowling. The results demonstrate that a nose-slot cowling may be successfully applied to an airplane and that it utilizes the increased slipstream velocity of low-speed operation to produce increased cooling pressure across the engine. A sample design calculation using results from wind-tunnel, flight, and ground tests is given in an appendix to illustrate the design procedure.
    Type: NACA-TN-720
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 99
    facet.materialart.
    Unknown
    Pressure-distribution measurements on a rectangular wing with a partial-span split flap in curved flight (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pressure-distribution tests were made on the 32-foot whirling arm of the Daniel Guggenheim Airship Institute of a rectangular wing of NACA 23012 section to determine the rolling and the yawing moment due to angular velocity in yaw. The model was tested at 0 and 5 degree pitch; 0, +/- 5, and +/- 10 degrees yaw; and with no flap and with split flaps 25, 50 and 75 percent of the wing span and deflected 60 degrees. The results are given in the form of span load distributions and as calculated moment coefficients. The experimental values of rolling- and yawing-moment coefficients were in fairly close agreement with theory.
    Type: NACA-TN-742
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 100
    facet.materialart.
    Unknown
    Observations in Flight of the Region of Stalled Flow over the Blades of an Autogiro Rotor (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The flow over the inner halves of the rotor blades on a Kellet YG-1B autogiro was investigated in flight by making camera records of the motion of silk streamers attached to the upper surfaces of the blades. These records were analyzed to determine the boundaries of the region within which the flow over the blade sections was stalled for various tip-speed ratios. For the sake of comparison, corresponding theoretical boundaries were obtained. Both the size of the stalled area and its rate of growth with increasing tip-speed ratio were found to be larger than the theory predicted, although experiment agreed with theory with regard to shape and general location of the stalled area. The stalled region may be an important factor in both the rotor lift-drag ratio and the blade flapping motion at the higher tip-speed ratios. The method of study used in this paper should be useful in further studies of the problem, including the reduction of the size of the region.
    Type: NACA-TN-741
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...