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
  • 1
    facet.materialart.
    Unknown
    [Neue Nr. 6013] Bingen-Rüdesheim / Geologische Karte (1930)
    Hessisches Landesamt für Bodenforschung, Wiesbaden
    In:  SUB Göttingen | KART B 104:6013 | KART H 86:6013
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: E 007 50 - E 008 00 / N 050 00 - N 049 54. GeoTIFF erstellt durch FID GEO, SUB Göttingen. Georeferenzierung basiert auf den Koordinaten: E 7°49'56"-E 7°59'57"/N 49°59'56"-N 49°53'55"
    Description: DFG, SUB Göttingen
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte ; Bingen ; Rüdesheim ; GeoTIFF
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 172
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    CITATION GEO-LEO
  • 2
    facet.materialart.
    Unknown
    Nochmals: Zur Frage der Laufzeitkurven (1930)
    In:  Zeitschrift für Geophysik, Milano, Gustav Fischer, vol. 6, no. 3, pp. 57-59, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Travel time ; Seismology
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 3
    facet.materialart.
    Unknown
    Schwere und Druck im Erdinnern (1930)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 26, no. 3, pp. 37-41, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Gravimetry, Gravitation ; Earth model, also for more shallow analyses !
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 4
    facet.materialart.
    Unknown
    Das Taunusbeben vom 22. Januar 1930 (1930)
    In:  Natur und Museum, Milano, Gustav Fischer, vol. 60, no. 3, pp. 147-151, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Seismology ; Earthquake
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 5
    facet.materialart.
    Unknown
    Hypothesen über die Entwicklung der Erde (1930)
    In:  Forschungen und Fortschritte, Milano, Gustav Fischer, vol. 6, no. 3, pp. 66-67, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Earth model, also for more shallow analyses ! ; Geothermics ; Tectonics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 6
    facet.materialart.
    Unknown
    Zur Frage der Erdbebenursachen (1930)
    In:  Forschungen und Fortschritte, Milano, Gustav Fischer, vol. 6, no. 3, pp. 133-135, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Seismology ; Earth model, also for more shallow analyses ! ; Seismicity
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 7
    facet.materialart.
    Unknown
    Registrierungen mit zwei Galitzin-Pendeln verschiedener Periode (1930)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 25, no. 3, pp. 74-80, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Instruments ; Seismology ; Seismometer
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 8
    facet.materialart.
    Unknown
    Die dynamische Vergrösserung von Schallregistrierungen für andauernde Sinuswellen (1930)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 26, no. 3, pp. 34-36, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Instruments ; Seismometer ; Seismology ; Acoustics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 9
    facet.materialart.
    Unknown
    Der Aufbau des Untergrundes im Pazifischen Ozean (1930)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 26, no. 3, pp. 156-157, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Earth model, also for more shallow analyses ! ; CRUST ; earth mantle
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 10
    facet.materialart.
    Unknown
    Die Verteilung der Massen an der Erdoberfläche - Bemerkungen zu dem Aufsatz von L. Kober (1930)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 26, no. 3, pp. 158-160, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Gravimetry, Gravitation ; Earth model, also for more shallow analyses !
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 11
    facet.materialart.
    Unknown
    Viskosität und innere Reibung fester Körper (1930)
    In:  Physikalische Zeitschrift, Milano, Gustav Fischer, vol. 31, no. 3, pp. 745-752, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Elasticity ; Rock mechanics ; Inelastic ; Rheology ; Friction
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 12
    facet.materialart.
    Unknown
    Schallgeschwindigkeit und Temperatur in der Stratosphäre (1930)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 27, no. 3, pp. 217-225, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Wave propagation ; Meteorology ; Acoustics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 13
    facet.materialart.
    Unknown
    Bemerkungen zu der vorstehenden Erwiderung von Herrn G. Krumbach (1930)
    In:  Zeitschrift für Geophysik, Milano, Gustav Fischer, vol. 6, no. 3, pp. 62-64, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: NOK
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 14
    facet.materialart.
    Unknown
    Bau und Bildung der Erdkruste (1930)
    In:  Neue Jahrbücher f. Wissenschaft und Jugendbildung, Milano, Gustav Fischer, vol. 6, no. 3, pp. 393-408, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: CRUST ; Earth model, also for more shallow analyses !
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 15
    facet.materialart.
    Unknown
    Hypotheses on the development of the earth (1930)
    In:  Journ. Wash. Acad. Sci., Milano, Gustav Fischer, vol. 20, no. 3, pp. 17-25, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Earth model, also for more shallow analyses ! ; Geothermics ; Tectonics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 16
    facet.materialart.
    Unknown
    The process of formation of seismic surface waves (1930)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 20, no. 3, pp. 11-14, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Surface waves ; Waves ; BSSA
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 17
    facet.materialart.
    Unknown
    Das Taunusbeben vom 22. Januar 1930 (1930)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 26, no. 3, pp. 141-155, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1930
    Keywords: Seismology ; Earthquake
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 18
    facet.materialart.
    Unknown
    An Introduction to the Study of Wave Mechanics (1930)
    In:  London, Wiley and Sons, vol. 2, no. 3, pp. 2-203, (ISBN 3-0521-81830-3)
    Details
    Publication Date: 1930
    Keywords: Textbook of physics ; Waves ; Wave propagation
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 19
    facet.materialart.
    Unknown
    Kräfte in der Erdkruste (1930)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 3: Veränderungen der Erdkruste (finished), 12 + 686 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1-31, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1930
    Keywords: Crustal deformation (cf. Earthquake precursor: deformation or strain) ; CRUST ; Review article ; Tectonics
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 20
    facet.materialart.
    Unknown
    Die Schäden des Winterwetters 1928/29 an den fremdländischen Holzarten des forstlichen Versuchsgartens in Grafrath bei München (1930)
    In:  Forstw. Centbl. 52 (2): 33-47
    Details
    Publication Date: 1930
    Description: Diskussion über die Schäden des kalten Winterwetters 1928/29 an den fremdländischen Holzarten des forstlichen Versuchsgartens in der Nähe von München. Eine Liste der betroffenen Baumarten ist vorhanden. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Grafrath bei München, Bayern ; 1928-1929
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 21
    facet.materialart.
    Unknown
    Die Wirkung des außergewöhnlich strengen Winters 1928-29 auf die Waldbäume (1930)
    In:  Ceskoslov. Akad. Zemedelske Vestnik 6: 274-278
    Details
    Publication Date: 1930
    Description: Bericht über die Auswikungen des strengen Winters 1928/29 auf Waldbäume in der Tschechischen Republik KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Tschechien ; 1928-1929
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 22
    facet.materialart.
    Unknown
    Agrarmetereologische Untersuchungen der Altmark auf Grund der Beziehungen zwischen Witterungsfaktoren und Ernteerträgen (1930)
    In:  Diss. Halle
    Details
    Publication Date: 1930
    Keywords: Altmark
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 23
    facet.materialart.
    Unknown
    Die Abhängigkeit der Zuckerrübenerträge und des Zuckergehaltes der Rüben von den Witterungsfaktoren im Gebiete zwischen Saale und Dübener Heide (1930)
    In:  Zuckerrübenbau 11:185-192.
    Details
    Publication Date: 1930
    Description: Auswertung von 27 Versuchsjahren, Bestimmung einer kritischen Periode für die Mindestniederschlagshöhe in Kombination mit niedrigen Temperaturen und Sonnenscheindauer mittels Rangkorrelationskoeffizienten KATASTER-BESCHREIBUNG: Zusammenhang zwischen der Niederschlagshöhe und dem Ertrag von Zuckerrüben, Zusammenhang zwischen der Sonnenscheindauer und dem Zuckergehalt von Zuckerrüben KATASTER-DETAIL: Delta Nied+: Nied 〉 175 mm (Juli-September), dann Ertragssteigerung bei ZR; Delta Sonn +: Sonn〉 4.43 h (September -Oktober), dann hohe Zuckergehalte bei ZR
    Keywords: Sachsen-Anhalt ; 1899-1926 ; Zuckerrüben ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Sonnenscheindauer
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 24
    facet.materialart.
    Unknown
    Some effects of artificial climates on the growth and chemical composition of plants. (1930)
    In:  American Journal of Botany 17:416-482.
    Details
    Publication Date: 1930
    Description: Zusammenhang Klima, Wachstum und Inhaltsstoffe von Pflanzen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: weltweit ; Ertrag
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 25
    facet.materialart.
    Unknown
    Effect of temperature on host reactions to physiologic forms of Puccinia graminis avenae, Erikss. & Henn. (1930)
    In:  Scient.Agr.11, p.95-103
    Details
    Publication Date: 1930
    Description: Laborversuche zum Einfluß von Temperaturen auf die Wechselwirkungen zwischen verschiedenen Unterarten von Puccinia graminis avenae und unterschiedlichen Getreidesorten. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Labor ; 1928-29 ; Getreide ; Pflanzenkrankheit
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 26
    facet.materialart.
    Unknown
    The relation of weather to plant diseases (1930)
    In:  Reprinted in Trop. Agr. 1930, p.353-378
    Details
    Publication Date: 1930
    Description: Review wichtiger Erkenntnisse der letzten Jahre über den Einfluß der Wettervariablen Temperatur, Feuchte, Luftfeuchte, Niederschlag, Licht und Wind auf verschiedene Schaderreger mit Fallbeispielen aus den Jahren 1904-1927 hauptsächlich aus den USA und Europa. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: USA, Europa ; 1904-1927 ; Pflanzenkrankheit ; Pflanzenschädling
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 27
    facet.materialart.
    Unknown
    Agrarmeteorologie: die Abhängigkeit der Ernteerträge von Wetter und Klima (1930)
    In:  P. Parey, Berlin.
    Details
    Publication Date: 1930
    Description: Abhängigkeit der Erträge von Erbsen, Kartoffeln, Winterweizen und Hafer und Winterroggen von Witterungseinflüssen mithilfe der Rangordnungs- und Korrelationsmethode KATASTER-BESCHREIBUNG: Mithilfe der Abweichungen von Rangordnungszahlen für die Temperatur und den Niederschlag für einzelne, bzw. 2 Monatsabschnitte, Summen für Zeiträume und Beziehungen zun Ertrag erfolgt die Bestimmung von kritischen Zeiten KATASTER-DETAIL: Delta T (März, April) + und Delta Nied (März, April) -, dann Erträge (Erbsen) +; Delta T (Mai, Juni) - und Delta Nied (Mai, Juni) +, dann Erträge (Erbsen) +; Delta T (Oktober - vorhergehendes Jahr) +, dann Erträge (Kartoffeln) +; Delta T (März)+, dann Erträge (Winterweizen) +; Delta T (Mai, Juni) -, dann Erträge (Winterweizen) +; Delta Nied (Januar bis März) -, dann Erträge (Hafer) +; Delta Nied (Januar bis März) -, dann Erträge (Winterroggen) +;
    Keywords: Deutschland ; 1930 ; Kartoffeln ; Ertrag ; Getreide ; Hafer ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Roggen ; Temperatur ; Weizen ; Witterung ; Erbsen
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 28
    facet.materialart.
    Unknown
    Die Häufigkeit nasser und dürrer Sommermonate im mittleren Norddeutschland (1930)
    In:  Der Kulturtechniker 33: 243-269
    Details
    Publication Date: 1930
    Keywords: Nord- und Mitteldeutschland ; 1900-1930
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 29
    facet.materialart.
    Unknown
    Die Beziehungen der Witterungsfaktoren zu den Ernteerträgen im Gebiet zwischen Magdeburg und Nordharz (1930)
    In:  Diss. Halle
    Details
    Publication Date: 1930
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 30
    facet.materialart.
    Unknown
    Geotektonische Hypothesen (1930)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 3: Veränderungen der Erdkruste (finished), 12 + 686 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 442-547, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1930
    Keywords: Tectonics ; Plate tectonics ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Review article
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 31
    facet.materialart.
    Unknown
    Identification of Aircraft Tubing by Rockwell Test (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Seamless steel tubing is today the principal material of construction for aircraft. The commercial grade of tubing containing about 0.10 to 0.20% carbon at first used is being superseded by two grades which are approved by the army and navy, and which are also becoming standard for commercial airplanes.
    Keywords: Aircraft Design, Testing and Performance
    Type: AD-B204801 , NASA-TM-111285 , NACA-TN-342 , NAS 1.15:111285
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 32
    facet.materialart.
    Unknown
    Bibliography of Aeronautics, 1929 (1930)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: This Bibliography of Aeronautics for 1929 covers the aeronautical literature published from January 1 to December 31, 1929. The first Bibliography of Aeronautics was published by the Smithsonian Institution as Volume 55 of the Smithsonian Miscellaneous Collections and covered the material published prior to June 30, 1909. Supplementary volumes of the Bibliography of Aeronautics for the subsequent years have been published by the National Advisory Committee for Aeronautics. The last preceding volume was for the calendar year 1928. As in the previous volumes, citations of the pUblications of all nations are included in th.e languages in which. these publications originally appeared. The arrangement is in dictionary form with author and subject entry, and one alphabetical arrangement. Detail in the matter of subject reference has been omitted on account of the cost of presentation, but an attempt has been made to give sufficient cross reference for research in special lines.
    Keywords: Aeronautics (General)
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 33
    facet.materialart.
    Unknown
    Measurement of profile drag on an airplane in flight by the momentum method. Part II (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this section is to survey the present status of scientific knowledge of the causes which produce drag, in order, if possible, to establish the relation between the individual results and the actual phenomena which demonstrate the fundamental importance of surface conditions. A discussion of the boundary layer is followed by: relations between frictional and form drag, application to profile-drag measurements, and different kinds of roughness. High-pressure wind tunnel tests are discussed along with roughness and maximum lift.
    Type: NACA-TM-558
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 34
    facet.materialart.
    Unknown
    Calculation of tapered monoplane wings (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tapered wing shape increases the lift in the middle of the wing and thus reduces the bending moment of the lifting forces in the plane of symmetry. Since this portion of the wing is the thickest, the stresses of the wing material are reduced and desirable space is provided for stowing the loads in the wing. This statically excellent form of construction, however, has aerodynamic disadvantages which must be carefully weighed, if failures are to be avoided. This treatise is devoted to the consideration of these problems.
    Type: NACA-TM-578
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 35
    facet.materialart.
    Unknown
    Effects of the end fixation of airplane struts (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The main purpose of this report is to give references to literature on the subject of end fixation of airplane struts and also to furnish the constructor with a general survey of the simplest methods for estimating the end-fixation effect.
    Type: NACA-TM-582
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 36
    facet.materialart.
    Unknown
    Gottingen six-component scale measurements on a Junkers A 35 airplane model (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The suggestion for the measurements collected in this report was prompted by the results of spinning experiments. For the theoretical spinning investigations there was a lack of data on lateral force, yawing, and rolling moment of airplanes.
    Type: NACA-TM-586
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 37
    facet.materialart.
    Unknown
    Metal Covering of Airplanes (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper presents a relative determination of the wrinkling of a plate wall beam with variable number of supports and methods of attachment. The discussion is based entirely on tests with extensometer readings and number of wrinkles, with complete web and with cutout sections. The author notes that the number of corrugations increase with added stress, keeping constant edge spacing.
    Type: NACA-TM-592
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 38
    facet.materialart.
    Unknown
    Practical Tests with the "auto Control Slot." Part II : Discussion (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For some time the D.V.L. has been investigating the question of applicability of Handley Page slotted wings to German airplanes. Comparitive gliding tests were made with open and closed slots on an Albatros L 75 airplane equipped with the Handley Page "auto control slots." This investigation served to determine the effect of the auto control slot on the properties and performances of airplanes at large angles of attack. The most important problems were whether the angle of glide at small angles of attack can be increased by the adoption of the auto control slot and, in particular, as to whether the flight characteristics at large angles of attack are improved thereby and equilibrium in gliding flight is guaranteed even at larger than ordinary angles of attack.
    Type: NACA-TM-594
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 39
    facet.materialart.
    Unknown
    Propulsion by Reaction (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report concerns propulsion by means of rockets. The author concerns himself mainly with efficiency of propulsion and he defines and mathematically expresses those efficiencies.
    Type: NACA-TM-571
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 40
    facet.materialart.
    Unknown
    Calculation of Pressure Distribution on Airship Hulls (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: These calculations were based on the shape of the ZR III, with the following simplifications: cars, fins, and rudders removed; all cross sections replaced by equivalent circular cross sections. Under these assumptions the pressure distribution was calculated for the following cases: symmetrical case, or flow parallel to the axis; unsymmetrical case, or flow at an angle to the axis. In both cases the simple potential flow first forms the basis for the determination of the pressure distribution.
    Type: NACA-TM-574
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 41
    facet.materialart.
    Unknown
    Practical Tests with the "auto Control Slot." Part I : Lecture (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For some time the D.V.L. has been investigating the question of applicability of Handley Page slotted wings to German airplanes. Comparitive gliding tests were made with open and closed slots on an Albatros L 75 airplane equipped with the Handley Page "auto control slots." This investigation served to determine the effect of the auto control slot on the properties and performances of airplanes at large angles of attack. The most important problems were whether the angle of glide at small angles of attack can be increased by the adoption of the auto control slot and, in particular, as to whether the flight characteristics at large angles of attack are improved thereby and equilibrium in gliding flight is guaranteed even at larger than ordinary angles of attack.
    Type: NACA-TM-593
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 42
    facet.materialart.
    Unknown
    Riveting in metal airplane construction. Part III : strength of riveted joints in duralumin (continued) (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report includes strength of riveted joints in duralumin, descriptions of test procedure and results of tests. Tabulated data includes: curshing strength by failure for various conditions, shearing strength of hole edge zone in direction of tearing, tearing strengths of plates weakened by rivet holes, and enlargement of holes at beginning of break.
    Type: NACA-TM-598
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 43
    facet.materialart.
    Unknown
    The torsional strength of wings (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes a simple method for calculating the position of the elastic axis of a wing structure having any number of spars. It is shown that strong drag bracing near the top and bottom of a wing greatly increases the torsional strength. An analytical procedure for finding the contribution of the drag bracing to the torsional strength and stiffness is described, based upon the principle of least work, and involving only one unknown quantity. A coefficient for comparing the torsional rigidity of different wings is derived in this report.
    Type: NACA-TR-329
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 44
    facet.materialart.
    Unknown
    Tests of Five Metal Model Propellers with Various Pitch Distributions in a Free Wind Stream and in Combination with Model VE-7 Fuselage (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the tests of five adjustable blade metal model propellers both in a free wind stream and in combination with a model fuselage with stub wings. The propellers are of the same form and cross section but have variations in radial distributions of pitch. By making a survey of the radial distribution of air velocity through the propeller plane of the model fuselage it was found that this velocity varies from zero at the hub center to approximately free stream velocity at the blade tip. The tests show that the efficiency of a propeller when operating in the presence of the airplane is, over the working range, generally less than when operating in a free wind stream, but that a propeller with a radial distribution of pitch of the same nature as the radial distribution of air velocity through the propeller plane suffers the smallest loss in efficiency.
    Type: NACA-TR-326
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 45
    facet.materialart.
    Unknown
    Simplified aerodynamic analysis of the cyclogiro rotating wing system (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simplified aerodynamic theory of the cyclogiro rotating wing is presented herein. In addition, examples have been calculated showing the effect on the rotor characteristics of varying the design parameters of the rotor. A performance prediction, on the basis of the theory here developed, is appended, showing the performance to be expected of a machine employing this system of sustentation. The aerodynamic principles of the cyclogiro are sound; hovering flight, vertical climb, and a reasonable forward speed may be obtained with a normal expenditure of power. Auto rotation in a gliding descent is available in the event of a power-plant failure.
    Type: NACA-TN-467
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 46
    facet.materialart.
    Unknown
    Identification of Aircraft by Rockwell Test (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A large number of tests were made on tubes of 1025 and 4130X steel, in various diameters and wall thicknesses, and after diverse heat treatments. The Rockwell B scale was employed, as being the best suited to the ranges of hardness encountered. Only satisfactory chrome molybdenum tubes were found to show a hardness in excess of 90-B after normalizing. The method therefore provided the desired means of identification of chrome molybdenum steel. It is a qualitative test only. The conditions of a satisfactory test are as follows. 1) The tubing must be normalized. 2) It must be clean inside and out at the point where the test is to be made. 3) The tube must be held in correct alignment with the penetrator and must not move during the test. 4) For thin-walled tubes, the anvil must extend within the tube so as to support the wall.
    Type: NACA-TN-342
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 47
    facet.materialart.
    Unknown
    Calibration and Lag of a Friez Type Cup Anemometer (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests on a Friez type cup anemometer have been made in the variable density wind tunnel of the Langley Memorial Aeronautical Laboratory to calibrate the instrument and to determine its suitability for velocity measurements of wind gusts. The instrument was calibrated against a Pitot-static tube placed directly above the anemometer at air densities corresponding to sea level, and to an altitude of approximately 6000 feet. Air-speed acceleration tests were made to determine the lag in the instrument reading. The calibration results indicate that there should be an altitude correction. It is concluded that the cup anemometer is too sluggish for velocity measurements of wind gusts.
    Type: NACA-TN-341
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 48
    facet.materialart.
    Unknown
    Full Scale Drag Tests on Various Parts of Fairchild (FC-2W2) Cabin Monoplane (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The drag due to the various parts of a Fairchild (FC-2W2) cabin monoplane was measured at air speeds varying from 50 to 100 m.p.h., in the Twenty-Foot Propeller Research Tunnel of the National Advisory Committee for Aeronautics. It was found that the largest drag was due to the radial air-cooled engine. The measured drag due to the landing gear was also large, being about 4/5 of that due to the engine. Substituting Musselman type wheels for the standard wheels caused no change in the drag due to the landing gear. A small decrease in drag was effected by adding a turtle back to the airplane fuselage.
    Type: NACA-TN-340
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 49
    facet.materialart.
    Unknown
    Refrigerated Wind Tunnel Tests on Surface Coatings for Preventing Ice Formation (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted to determine the effectiveness of various surface coatings as a means for preventing ice formations on aircraft in flight. The substances used as coatings for these tests are divided into two groups: compounds soluble in water, and those which are insoluble in water. It was found that certain soluble compounds were apparently effective in preventing the formation of ice on an airfoil model, while all insoluble compounds which were tested were found to be ineffective.
    Type: NACA-TN-339
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 50
    facet.materialart.
    Unknown
    Some Effects of Air and Fuel Oil Temperatures on Spray Penetration and Dispersion (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Presented here are experimental results obtained from a brief investigation of the appearance, penetration, and dispersion of oil sprays injected into a chamber of highly heated air at atmospheric pressure. The development of single sprays injected into a chamber containing air at room temperature and at high temperature was recorded by spray photography equipment. A comparison of spray records showed that with the air at the higher temperature, the spray assumed the appearance of thin, transparent cloud, the greatest part of which rapidly disappeared from view. With the chamber air at room temperature, a compact spray with an opaque core was obtained. Measurements of the records showed a decrease in penetration and an increase in the dispersion of the spray injected into the heated air. No ignition of the fuel injected was observed or recorded until the spray particles came in contact with the much hotter walls of the chamber about 0.3 second after the start of injection.
    Type: NACA-TN-338
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 51
    facet.materialart.
    Unknown
    Pressure distribution on the tail surfaces of a PW-9 pursuit airplane in flight (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Presented here are pressure distribution data obtained from the tail surfaces of a PW-9 in a number of flight maneuvers. The results given are part of those obtained in an extensive investigation of the pressure distribution over all of the lifting and control surfaces of this airplane. The results are given in tabular and curve form and are discussed briefly with respect to their comparison with existing tail surface design specifications. It is recommended that tail load design loadings should be revised upwards. This is particularly true of leading edge loads, which should be at least doubled for thick sections.
    Type: NACA-TN-337
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 52
    facet.materialart.
    Unknown
    The Effect of Wing Tip Floating Ailerons on the Autorotation of a Monoplane Wing Model (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The preliminary tests described here were made to determine the extent to which wing tip floating ailerons might be effective in reducing airplane spinning tendencies. The tests showed that initial spinning tendencies and rates of stable spinning could doubtless be reduced by the use of tip floating ailerons on an airplane. It also appears to be desirable to reduce to a minimum the interference between wing and aileron. This would serve to maintain uniformity of action at all angles of attack and enable calculation of the aileron characteristics.
    Type: NACA-TN-336
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 53
    facet.materialart.
    Unknown
    The Structure and Properties of Parachute Cloths (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The requisite properties of a parachute cloth are discussed and the methods for measuring these properties described. In addition to the structural analysis of the cloths, the properties measured were weight, breaking strength, tear resistance, elasticity, and air permeability. Thirty-six silk cloths of domestic manufacture, not previously used in parachute construction are compared with some silk cloths of foreign manufacture. These foreign cloths were ones proven by trial and extended use to be suitable materials for parachute construction. Contrary to the belief that domestic woven cloths were not suitable materials for parachute construction, it is shown that many domestic silk cloths are satisfactory and in some respects superior to the foreign products. Based on a comparative study of all the cloths, specifications are drawn for the manufacture of silk parachute cloth.
    Type: NACA-TN-335
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 54
    facet.materialart.
    Unknown
    Comparative Performance Obtained with XF7C-1 Airplane Using Several Different Engine Cowlings (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Discussed here are problems with the use of cowlings with radial air cooled engines. An XF7C-1 airplane, equipped with service cowling and with narrow ring, wide ring, and exhaust collector ring cowlings over the service cowling, was used. For these four cowling conditions, the rate of climb and high speed performance were determined, the cylinder conditions were measured, and pictures to show visibility were taken. The level flight performance obtained with an engine speed of 1900 r.p.m. for the service type, the narrow ring, the wide ring, and the exhaust collector ring was 144.4, 146.6, 152.8, and 155 mph, respectively. The rate of climb was practically the same for each type tested. The visibility was not materially impaired by the use of the wide or the narrow cowlings. With the narrow ring and exhaust collector ring cowlings there was an increase in cylinder temperature. However, this increase was not enough to affect the performance of the engine. The use of an exhaust collector ring incorporated into the cowling is practical where the problem of visibility does not enter.
    Type: NACA-TN-334
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 55
    facet.materialart.
    Unknown
    Test of an adjustable pitch model propeller at four blade settings (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note describes tests of an adjustable blade metal model propeller, both in a free wind stream and in combination with a model fuselage, at four settings of the blades. The model propeller is designed for a uniform nominal pitch/diameter ratio of .7 and the blade settings used correspond to nominal pitch/diameter ratios of .5, .7, .9, and 1.1 at the .6 radius. The tests show that propellers of this type may be considerably changed in setting from the designed pitch angles and yet give excellent performance. The efficiency realized and power absorbed when blades are set at other than the designed angle, are little different than would be obtained from a propeller with uniform pitch equal to the mean pitch of the propeller under test.
    Type: NACA-TN-333
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 56
    facet.materialart.
    Unknown
    Injection Labs in a Common-Rail Fuel Injection System (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-332
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 57
    facet.materialart.
    Unknown
    Rate of Heat Transfer from Finned Metal Surfaces (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The object was to evaluate the factors which control the rate of heat transfer to a moving current of air from finned metal surfaces similar to those used on aircraft engine cylinders. The object was to establish data which will enable the finning of cooling surfaces to be designed to suit the particular needs of any specific application. Most of the work was done on flat copper specimens 6 inches square, upon which were mounted copper fins with spacings varying from 1/2 inch to 1/12 inch. All fins were 1 inch deep, 6 inches long, and .020 inch thick. The results of the investigation are given in the form of curves included here. In general, it was found that for specimens of this kind, the effectiveness of a given fin does not decrease very rapidly until its distance from adjacent fins has been reduced to 1/9 or 1/10 of an inch. A formula for the heat transfer from a flat surface without fins was developed, and an approximate formula for the finned specimens is suggested.
    Type: NACA-TN-331
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 58
    facet.materialart.
    Unknown
    A Balanced Diaphragm Type of Maximum Cylinder Pressure Indicator (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A balanced diaphragm type of maximum cylinder pressure indicator was designed to give results consistent with engine operating conditions. The apparatus consists of a pressure element, a source of controlled high pressure and a neon lamp circuit. The pressure element, which is very compact, permits location of the diaphragm within 1/8 inch of the combustion chamber walls without water cooling. The neon lamp circuit used for indicating contact between the diaphragm and support facilitates the use of the apparatus with multicylinder engines.
    Type: NACA-TN-359
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 59
    facet.materialart.
    Unknown
    Experiments with a Model Water Tunnel (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes a model water tunnel built in 1928 by the NACA to investigate the possibility of using water tunnels for aerodynamic investigations at large scales. The model tunnel is similar to an open-throat wind tunnel, but uses water for the working fluid.
    Type: NACA-TN-358
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 60
    facet.materialart.
    Unknown
    Bending Tests of Metal Monocoque Fuselage Construction (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This thesis presents a study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameters to thickness. The test specimens - circular, thin-walled cylinder were loaded to give a large bending stress in proportion to the shearing stress, in order to represent the critical section of a fuselage.
    Type: NACA-TN-357
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 61
    facet.materialart.
    Unknown
    Some Characteristics of Fuel Sprays from Open Nozzles (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The penetration and cone-angle of fuel sprays from open nozzles were recorded with the NACA Spray Photography Equipment. The results show that for injection systems in which the rate of pressure rise at the discharge orifice is high, open nozzles give spray-tip velocities and penetrations which compare favorably with those of closed nozzles. The spray cone-angle was the same for all tests, although open nozzles having different orifice diameters were used, and one nozzle was used both as an open and as a closed nozzle. In designing a fuel system using open nozzles, particular care must be taken to avoid air pockets. The check valve should be placed close to the discharge orifice.
    Type: NACA-TN-356
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 62
    facet.materialart.
    Unknown
    Effect of the Angular Position of the Section of a Ring Cowling on the High Speed of an XF7C-1 Airplane (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests herein reported were conducted by the NACA to determine the effect of the angular position of the section of a ring cowling on the speed of an airplane having a radial air-cooled engine.
    Type: NACA-TN-355
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 63
    facet.materialart.
    Unknown
    An Investigation of the Phenomenon of Separation in the Air Flow Around Simple Quadric Cylinders (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests, conducted at the Guggenheim Aeronautical Laboratory of Stanford University, to investigate the phenomenon of separation in the air flow past geometric shapes are described in this report.
    Type: NACA-TN-354
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 64
    facet.materialart.
    Unknown
    Analytical determination of the load on a trailing edge flap (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a theoretical analysis of the lift on a trailing edge flap. An analytical expression has been derived which enables the computation of the flap load coefficient. The theoretical results seem to show a fair agreement with the meager experimental results which are available.
    Type: NACA-TN-353
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 65
    facet.materialart.
    Unknown
    An accurate method of measuring the moments of inertia of airplanes (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note contains a description of an improved apparatus and procedure used by the NACA for determining the moments of inertia of airplanes. The method used, based on the pendulum theory, is similar to that previously used, but a recent investigation of its accuracy has resulted in the improvements described herein. The error, when using the new apparatus and procedure, has been found to be of the order of 1 per cent.
    Type: NACA-TN-351
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 66
    facet.materialart.
    Unknown
    Effect of Orifice Length-Diameter Ratio on Spray Characteristics (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of variations of orifice length to diameter ratio on spray characteristics was determined for a 0.014-inch and a 0.040-inch orifice for ratio of 0.5 to 4.0. The nozzles containing the orifices were mounted in an injection valve and tested with a plan stem and with a helically grooved stem. The injection pressure was varied from 4000 to 8000 pounds per square inch. The air density into which the fuel was sprayed was varied from the density obtained with a pressure of 60 pounds per square inch to the density obtained with a pressure of 250 pounds per square inch at room temperature. The tests showed that increasing the orifice length to diameter ratio with a plain stem in the injection valve causes the spray tip penetration first to decrease, reaching a minimum between a ratio of 1.5 and 2.5, and then to increase, reaching a maximum at a ratio greater than 3.5. The spray cone angle showed little change with variation of the ratio. With a helically grooved stem and small ratio of orifice area to groove area, the penetration at first shows little tendency towards a minimum; but as the time of injection is increased to 0.004 second, the penetration becomes a minimum at a ratio between 0.5 and 2.0.
    Type: NACA-TN-352
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 67
    facet.materialart.
    Unknown
    Methods for the Identification of Aircraft Tubing of Plain Carbon Steel and Chromium-Molybdenum Steel (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The survey of the possibilities for distinguishing between plain carbon and chromium-molybdenum steel tubing included the Herbert pendulum hardness, magnetic, sparks, and chemical tests. The Herbert pendulum test has the disadvantages of all hardness tests in being limited to factory use and being applicable only to scale-free, normalized material. The small difference in the range of hardness values between plain carbon and chromium-molybdenum steels is likewise a disadvantage. The Rockwell hardness test, at present used in the industry for this purpose, is much more reliable. It may be concluded on the basis of the experiments performed that of all methods surveyed, spark testing appears to be, at present, the most suitable for factory use from the standpoint of speed, accuracy, nondestructiveness and reliability. It is also applicable for field use.
    Type: NACA-TN-350
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 68
    facet.materialart.
    Unknown
    An Investigation of Airplane Landing Speeds (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper describes an investigation on airplane landing speeds which was made to determine the applicability of accepted aerodynamic theory to the prediction of this particular performance characteristic. The experimental work consisted in measuring the landing speed of several monoplanes by a new photographic method. The results of these tests supplemented by available information regarding biplanes were compared with predictions made with basic aerodynamic theory. The prediction makes use of the fundamental relation between wing loading, lift coefficient, and speed of level flight, and the effects of aspect ratio and proximity to the ground on lift curve slope.
    Type: NACA-TN-349
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 69
    facet.materialart.
    Unknown
    Alterations and Tests of the "Farnboro" Engine Indicator (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The 'Farnboro' electric indicator was tested as received from the manufacturers, and modifications made to the instrument to improve its operation. The original design of disk valve was altered so as to reduce the mass, travel, and seat area. Changes were made to the recording mechanism, which included a new method of locating the top center position on the record. The effect of friction on the motion of the pointer while taking motoring and power cards was eliminated by providing a means of putting pressure lines on the record. The modified indicator gives a complete record of the average cyclic variation in pressure per crank degree for any set of engine operating conditions which can be held constant for the period of time required to build up the composite card. The value of the record for accurate quantitative measurement is still questioned, although the maximum indicated pressure recorded on the motoring and power cards checks the readings of the balanced diaphragm type of maximum cylinder pressure indicator.
    Type: NACA-TN-348
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 70
    facet.materialart.
    Unknown
    Pressure distribution over a Douglas wing tip on a biplane in flight (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note presents the results obtained in pressure distribution tests on the right upper wing panel and tip of a Douglas M-3 airplane in flight. These tests are a part of a more extensive investigation of the effect of changes in tip shape on the load distribution, the tip reported herein being the first of a series of tip shapes being tested. The results are given in tables and curves in such form that the load distribution for any conditions may be determined easily. Tests were made at Langley Field by the NACA in the spring of 1930.
    Type: NACA-TN-347
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 71
    facet.materialart.
    Unknown
    Span Load Distribution on Two Monoplanes Wing Models as Affected by Twist and Sweepback (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results presented in this note show the effect of twist and sweepback on the span load distribution over two monoplane wing models. The tests were made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. The data are taken from the results of an investigation dealing primarily with lateral stability. As presented, they are suitable as an aid in the structural design of certain monoplane wings.
    Type: NACA-TN-346
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 72
    facet.materialart.
    Unknown
    The Prevention of the Ice Hazard on Airplanes (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A review of various methods to prevent ice formation and adhesion to aircraft surfaces is given. It was concluded that the adhesion of ice to a surface may be reduced somewhat by the application of certain waxes and varnishes. In the experiments described, the varnishes containing calcium stearate and calcium oleate gave the best results. In wind tunnel tests, the adhesion was further reduced by the application of these waxes and varnishes to a thin, heat insulating layer of rubber. The adhesion of ice is greatly reduced when the surface consists of a vehicle which carries an oil in sufficient quantity so that the surface of the vehicle is self lubricating. Ice may be removed from wings, struts, wires and other parts of an airplane during flight by the inflation of properly constructed pneumatic rubber members, providing that these members have been previously treated with a suitable low adhesion oil.
    Type: NACA-TN-345
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 73
    facet.materialart.
    Unknown
    Performance of a High-Speed Compression-Ignition Engine Using Multiple Orifice Fuel Injection Nozzles (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents test results obtained at the Langley Memorial Aeronautical Laboratory of the National Advisory Committee for Aeronautics during an investigation to determine the relative performance of a single-cylinder, high-speed, compression-ignition engine when using fuel injection valve nozzles with different numbers, sizes, and directions of round orifices. A spring-loaded, automatic injection valve was used, centrally located at the top of a vertical disk-type combustion chamber formed between horizontally opposed inlet and exhaust valves of a 5 inch by 7 inch engine.
    Type: NACA-TN-344
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 74
    facet.materialart.
    Unknown
    Strength in Shear of the Thin Curved Sheets of Alclad (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is on an investigation made to obtain information on the strength of thin curved sheets of Alclad in shear. Designers may utilize this material as a strength member as well as for a covering for the wings and fuselages. A reduction may then be made in the size of the internal strength members. These experiments were undertaken with the object of securing the maximum value from the metal in this respect. The point at which buckling occurs is of primary importance. The buckling shear of a curved thin plate was determined mathematically and also experimentally. The following formula was obtained mathematically: s=K E t/r in which s is the unit shear, K is a constant, E is the modulus of elasticity, t is the thickness of the material, and r is the radius of curvature. The value of K as determined by the experiments was found to be .075. This formula applies only when s is within the elastic limit of the material. The breaking point of the material was obtained in most of the tests as a matter of information and the results are included in this report. The effect of the supporting ribs was determined by varying the number used.
    Type: NACA-TN-343
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 75
    facet.materialart.
    Unknown
    The electrodynamometric balance of the small wind tunnel of the French Service of Aeronautical Research (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation shows the attempt to improve the electrodynamomoter designed by Mr. Villey. The force to be measured acts on a flexible steel plate which is placed in front of a fixed plate. The deformation varies the original thickness of the layer of air between the two plates, thus causing a more rapid variation in the coefficient of electrostatic attraction of the two plates than in the capacity of the condenser formed by the dynamometer. The measurements are made by a differential method. The capacity of the test dynamometer is compared with that of a similar instrument of constant capacity, this comparison being made by means of an electrometer. Diagrams are shown of the dynamometer, the electrometer, and the electrical connections.
    Type: NACA-TM-556
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 76
    facet.materialart.
    Unknown
    The 1929 Rhon soaring-flight contest (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The limitation of the 1929 contest to performance gliders necessitated the establishment of a formula which would make it possible to distinguish between performance gliders and school and training gliders. The sinking speed was therefore adopted as the basis for such a distinction, and the requirement was made that the sinking speed of a performance glider should not exceed 0.8 m/s. The rest of the report details the different entries with regard to design and performance.
    Type: NACA-TM-560
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 77
    facet.materialart.
    Unknown
    Ratier Metal Propeller with Pitch Variable in Flight (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: One of the serious sources of difficulties in variable pitch propellers is the turning moment or torque due to the centrifugal force which tends to bring the mean plane of the blades into the plane of rotation. This moment, which is found elsewhere only in propellers with removable blades, is so great that the aerodynamic forces, as regards their effect on the torsion, become entirely negligible in comparison with it. This report presents the Ratier Company's solution to changing the pitch of airplane propellers.
    Type: NACA-TM-559
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 78
    facet.materialart.
    Unknown
    Balanced and servo control surfaces (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Many reports on various control systems are available, but the results cannot be generally applied since the effect of particular changes of surface-form and mounting are subject to variations depending upon airfoil section and influences of airplane layout. This report presents a simple analysis of several control systems in more general use. Elevators, ailerons, and rudders are all discussed.
    Type: NACA-TM-563
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 79
    facet.materialart.
    Unknown
    Recent tests of tailless airplanes (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report details the advantages and construction of tailless airplanes. Both a glider and a powered model were built and the specifications of both airplanes are listed.
    Type: NACA-TM-564
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 80
    facet.materialart.
    Unknown
    Development of the Junkers-diesel Aircraft Engine (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The working process of the Junkers engine has resulted from a series of attempts to attain high performance and to control the necessarily rapid and complete combustion at extremely high speeds. The two main problems of Diesel engines in aircraft are addressed; namely, incomplete combustion and the greater weight of Diesel engine parts compared to gasoline engines.
    Type: NACA-TM-565
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 81
    facet.materialart.
    Unknown
    The Magnus Effect in Theory and in Reality (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A discussion of the Flettner rotor is presented from a nautical and economic viewpoint, and although it was a failure, the experimental and theoretical inventions cannot be disregarded. The following critical and experimental investigation will show the relations and applicability of the theories and practical applications. The Magnus effect is described in detail and a discussion and critical review of the Magnus effect is included.
    Type: NACA-TM-567
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 82
    facet.materialart.
    Unknown
    Experimental research on the friction of pivots (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In horology the friction between solids is of the greatest importance; one limited, however, to the application of the laws of Coulomb which, do not at all correspond with reality. This report presents a review of the subject and some general conclusions. The choice of lubricant is discussed as well as the pressure between frictional surfaces. The gears in a watch are used extensively as examples.
    Type: NACA-TM-566
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 83
    facet.materialart.
    Unknown
    Contribution to the theory of propeller vibrations (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a calculation of the torsional frequencies of revolving bars with allowance for the air forces. Calculation of the flexural or bonding frequencies of revolving straight or tapered bars in terms of the angular velocity of revolution. Calculation on the basis of Rayleigh's principle of variation. There is also a discussion of error estimation and the accuracy of results. The author then provides an application of the theory to screw propellers for airplanes and the discusses the liability of propellers to damage through vibrations due to lack of uniform loading.
    Type: NACA-TM-568
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 84
    facet.materialart.
    Unknown
    A possible method for preventing the autorotation of airplane wings (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: At the suggestion of Professor Betz, the following device was tested with the object of reducing the autorotational speed of airplane wings. The model of a normal wing with the Gottigen profile 420, 1 meter span and 0.2 meter chord was provided with a pair of symmetrical slots on the suction side, connected with each other inside the wing. The arrangement of the testing equipment and models are given and the effect of the slots can be seen in the experimental curves that are included.
    Type: NACA-TM-569
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 85
    facet.materialart.
    Unknown
    "Gloster" metal construction (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report details the methods of construction employed by the Gloster Company in their fabrication of metal aircraft parts. Ribs, spars, wings, and metal treatments to prevent oxidation are all discussed.
    Type: NACA-TM-570
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 86
    facet.materialart.
    Unknown
    Determination of the Best Cross Section for a Box Beam Subjected to Bending Stresses (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Previous investigations on the strength characteristics and structure of wood in construction are analyzed and a method of representation is developed suitable for the use of designers.
    Type: NACA-TM-577
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 87
    facet.materialart.
    Unknown
    Determination of the Maximum Control Forces and Attainable Quickness in the Operation of Airplane Controls (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is intended to furnish bases for load assumptions in the designing of airplane controls. The maximum control forces and quickness of operation are determined. The maximum forces for a strong pilot with normal arrangement of the controls is taken as 1.25 times the mean value obtained from tests with twelve persons. Tests with a number of persons were expected to show the maximum forces that a man of average strength can exert on the control stick in operating the elevator and ailerons and also on the rudder bar. The effect of fatigue, of duration and of the nature (static or dynamic) of the force, as also the condition of the test subject (with or without belt) were also considered.
    Type: NACA-TM-583
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 88
    facet.materialart.
    Unknown
    Diesel-engine investigations : ignition-chamber engines (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a thorough investigation of the functioning process and injection and combustion characteristics of ignition-chamber engines.
    Type: NACA-TM-589
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 89
    facet.materialart.
    Unknown
    Riveting in metal airplane construction. Part IV : strength of riveted joints in duralumin (concluded) (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made to determine the crushing strength of a riveted joint, in order to define the difference in crushing stregth between a strictly bolted joint and a riveted joint. The object was to tabulate the crushing strength by failure on various plate thicknesses for a one-rivet double-shear riveted joint.
    Type: NACA-TM-599
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 90
    facet.materialart.
    Unknown
    The Torsion of Members Having Sections Common in Aircraft Construction (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Within recent years a great variety of approximate torsion formulas and drafting-room processes have been advocated. In some of these, especially where mathematical considerations are involved, the results are extremely complex and are not generally intelligible to engineers. The principal object of this investigation was to determine by experiment and theoretical investigation how accurate the more common of these formulas are and on what assumptions they are founded and, if none of the proposed methods proved to be reasonable accurate in practice, to produce simple, practical formulas from reasonably correct assumptions, backed by experiment. A second object was to collect in readily accessible form the most useful of known results for the more common sections. Formulas for all the important solid sections that have yielded to mathematical treatment are listed. Then follows a discussion of the torsion of tubular rods with formulas both rigorous and approximate.
    Type: NACA-TR-334
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 91
    facet.materialart.
    Unknown
    Experimental and Analytical Determination of the Motion of Hydraulically Operated Valve Stems in Oil Engine Injection Systems (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This research on the pressure variations in the injection system of the N.A.C.A. Spray Photography Equipment and on the effects of these variations on the motion of the timing valve stem was undertaken in connection with the study of fuel injection systems for high-speed oil engines. The methods of analysis of the pressure variations and the general equation for the motion of the spring-loaded stem for the timing valve are applicable to a spring-loaded automatic injection valve, and in general to all hydraulically operated valves. A sample calculation for a spring-loaded automatic injection valve is included.
    Type: NACA-TR-330
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 92
    facet.materialart.
    Unknown
    The Effect of Supercharger Capacity on Engine and Airplane Performance (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine the effect of different supercharger capacities on the performance of an airplane and its engine . The tests were conducted on a DH4-M2 airplane powered with a Liberty 12 engine. In this investigation four supercharger capacities, obtained by driving a roots type supercharger at 1.615, 1.957, 2.4, and 3 time engine speed, were used to maintain sea-level pressure at the carburetor to altitudes of 7,000, 11,500, 17,000, and 22,000 feet, respectively. The performance of the airplane in climb and in level flight was determined for each of the four supercharger drive ratios and for the unsupercharged condition. The engine power was measured during these tests by means of a calibrated propeller. It was found that very little sacrifice in sea-level performance was experienced with the larger supercharger drive ratios as compared with performance obtained when using the smaller drive ratios. The results indicate that further increase in supercharger capacity over that obtained when using 3:1 drive ratio would give a slight increase in ceiling and in high-altitude performance but would considerably impair the performance for an appreciable distance below the critical altitude. As the supercharger capacity was increased, the height at which sea-level high speeds could be equaled or improved became a larger percentage of the maximum height of operation of the airplane.
    Type: NACA-TR-327
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 93
    facet.materialart.
    Unknown
    Investigation of air flow in open-throat wind tunnels (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted on the 6-inch wind tunnel of the National Advisory Committee for Aeronautics to form a part of a research on open-throat wind tunnels. The primary object of this part of the research was to study a type of air pulsation which has been encountered in open-throat tunnels, and to find the most satisfactory means of eliminating such pulsations. In order to do this it was necessary to study the effects of different variable on all of the important characteristics of the tunnel. This paper gives not only the results of the study of air pulsations and methods of eliminating them, but also the effects of changing the exit-cone diameter and flare and the effects of air leakage from the return passage. It was found that the air pulsations in the 6-inch wind tunnel could be practically eliminated by using a moderately large flare on the exit cone in conjunction with leakage introduced by cutting holes in the exit cone somewhat aft of its minimum diameter.
    Type: NACA-TR-322
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 94
    facet.materialart.
    Unknown
    Aerodynamic Characteristics of Twenty-Four Airfoils at High Speeds (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic characteristics of 24 airfoils are given for speeds of 0.5, 0.65, 0.8, 0.95, and 1.08 times the speed of sound, as measured in an open-jet air stream 2 inches in diameter, using models of 1-inch chord. The 24 airfoils belong to four general groups. The first is the standard R. A. F. family in general use by the Army and Navy for propeller design, the members of the family differing only in thickness. This family is represented by nine members ranging in thickness from 0.04 to 0.20 inch. The second group consists of five members of the Clark Y family, the members of the family again differing only in thickness. The third group, comprising six members, is a second R. A. F. Family in which the position of the maximum ordinate is varied. Combined with two members of the first R.A.F. family, this group represents a variation of maximum ordinate position from 30 to 60 percent of the chord in two camber ratios, 0.08 and 0.16. The fourth group consists of three geometrical forms, a flat plate, a wedge, and a segment of a right circular cylinder. In addition one section used in the reed metal propeller was included. These measurements form a part of a general program outlined at a Conference on Propeller Research organized by the National Advisory Committee for Aeronautics and the work was carried out with the financial assistance of the committee (author)
    Type: NACA-TR-319
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 95
    facet.materialart.
    Unknown
    Aerodynamic Theory and Tests of Strut Forms-II (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the second of two studies under the same title. In this part five theoretical struts are developed from distributed sources and sinks and constructed for pressure and resistance tests in a wind tunnel. The surface pressures for symmetrical inviscid flow are computed for each strut from theory and compared with those found by experiment. The theoretical and experimental pressures are found to agree quantitatively near the bow, only qualitatively over the suction range, the experimental suctions being uniformly a little low, and not at all near the stern. This study is the strut sequel to Fuhrmann's research on airship forms, the one being a study in two dimensions, the other in three. A comparison of results indicates that the agreement between theory and experiment is somewhat better for bodies of revolution than for cylinders when both are shaped for slight resistance. The consistent deficiency of the experimental suctions which is found in the case of struts was not found in the case of airships, for which the experimental suctions were sometimes above sometimes below their theoretical values.
    Type: NACA-TR-335
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 96
    facet.materialart.
    Unknown
    Full-Scale Turning Characteristics of the U.S.S. Los Angeles (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper present a description of the method employed and results obtained in full-scale turning trials on the rigid airship U. S. S. "Los Angeles". The results of this investigation are not sufficiently comprehensive to permit definite conclusions as to the variation of turning characteristics with changes in speed and rudder angle. They indicate however, that the turning radius compares favorably with that for other large airships, that the radius is independent of the speed, that the position of the point of zero yaw is nearly independent of the rudder angle and air speed, and that a theoretical relation between radius and angle of yaw in a turn gives a close approximation to actuality.
    Type: NACA-TR-333
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 97
    facet.materialart.
    Unknown
    Collection of wind-tunnel data on commonly used wing sections (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report groups in a uniform manner the aerodynamic properties of commonly used wing sections as determined from tests in various wind tunnels. The data have been collected from reports of a number of laboratories. Where necessary, transformation has been made to the absolute system of coefficients and tunnel wall interference corrections have been applied. Tables and graphs present the data in the various forms useful to the engineer in the selection of a wing section.
    Type: NACA-TR-331
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 98
    facet.materialart.
    Unknown
    Water Pressure Distribution on a Twin-Float Seaplane (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This is the second of a series of investigations to determine water pressure distribution on various types of seaplane floats and hulls, and was conducted on a twin-float seaplane. It consisted of measuring water pressures and accelerations on a TS-1 seaplane during numerous landing and taxiing maneuvers at various speeds and angles. The results show that water pressures as great as 10 lbs. per sq. in.may occur at the step in various maneuvers and that pressures of approximately the same magnitude occur at the stern and near the bow in hard pancake landings with the stern way down. At the other parts of the float the pressures are less and are usually zero or slightly negative for some distance abaft the step. A maximum negative pressure of 0.87 lb. Per square inch was measured immediately abaft the step. The maximum positive pressures have a duration of approximately one-twentieth to one-hundredth second at any given location and are distributed over a very limited area at any particular instant.
    Type: NACA-TR-328
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 99
    facet.materialart.
    Unknown
    Flight Tests on U.S.S. Los Angeles. Part II : Stress and Strength Determination (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests described in this report furnished data on the actual aerodynamic forces, and the resulting stresses and bending moments in the hull of the U. S. S. "Los Angeles" during as severe still-air maneuvers as the airship would normally be subjected to, and in straight flight during as rough air as is likely to occur in service, short of squall or storm conditions. The maximum stresses were found to be within the limits provided for in accepted practice in airship design. Normal flight in rough air was shown to produce forces and stresses about twice as great as the most severe still-air maneuvers. No light was thrown upon the forces which might occur in extreme or exceptional conditions, such as the storm which destroyed the "Shenandoah". The transverse aerodynamic forces on the hull proper were found to be small and irregular. Owing to the necessity of conserving helium, it was impossible to fly the airship in a condition of large excess of buoyancy or weight in order to determine the air pressure distribution at a fixed angle of pitch. However, there is every reason to believe that in that condition the forces on the actual airship are as close to the wind-tunnel results as can be determined by present type of pressure measuring apparatus. It is considered that most important data obtained are the coefficients of tail-surface forces and hull-bending moments. These are tabulated in this report.
    Type: NACA-TR-325
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 100
    facet.materialart.
    Unknown
    Flow and Force Equations for a Body Revolving in a Fluid (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Part I gives a general method for finding the steady-flow velocity relative to a body in plane curvilinear motion, whence the pressure is found by Bernoulli's energy principle. Integration of the pressure supplies basic formulas for the zonal forces and moments on the revolving body. Part II, applying this steady-flow method, finds the velocity and pressure at all points of the flow inside and outside an ellipsoid and some of its limiting forms, and graphs those quantities for the latter forms. Part III finds the pressure, and thence the zonal force and moment, on hulls in plane curvilinear flight. Part IV derives general equations for the resultant fluid forces and moments on trisymmetrical bodies moving through a perfect fluid, and in some cases compares the moment values with those found for bodies moving in air. Part V furnishes ready formulas for potential coefficients and inertia coefficients for an ellipsoid and its limiting forms. Thence are derived tables giving numerical values of those coefficients for a comprehensive range of shapes.
    Keywords: Aerodynamics
    Type: NACA-TR-323
    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...