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  • Weitere Quellen  (46)
  • Aerodynamics  (24)
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  • 2010-2014
  • 1950-1954  (25)
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  • 1950  (25)
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  • 2010-2014
  • 1950-1954  (25)
  • 1940-1944  (21)
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  • 1
    facet.materialart.
    Unbekannt
    Das Tibet-Beben vom 15. August 1950 (1950)
    In:  Geologische Rundschau, Milano, California Institute of Technology Pasadena, vol. 38, no. 6, pp. 164, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1950
    Schlagwort(e): Seismology ; Earthquake ; Seismicity ; China
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 2
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    Earthquakes in North America (1950)
    In:  Science, Milano, California Institute of Technology Pasadena, vol. 111, no. 6, pp. 319-324, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1950
    Schlagwort(e): Seismology ; Seismicity
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 3
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    Unbekannt
    Wave velocities in the earth's crustal layers (1950)
    In:  Geophysics, Milano, California Institute of Technology Pasadena, vol. 15, no. 6, pp. 156, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1950
    Schlagwort(e): Waves ; Velocity analysis ; Seismology
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 4
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    Unbekannt
    Progress report, Seismological Laboratory, California Institute of Technology, 1949 (1950)
    In:  Trans. Am. Geophys. Union, Beijing, Pergamon, vol. 31, no. 3-4, pp. 463-467, pp. 1246
    Details
    Publikationsdatum: 1950
    Schlagwort(e): Seismology ; Project report/description ; EOS
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 5
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    An earth model based on a compressibility-pressure hypothesis (1950)
    In:  Monthly Not. R. astr. Soc., Geophys., Tulsa, 3-4, vol. Suppl. 6, no. 1, pp. 50-59, pp. B09405, (ISBN: 0-12-018847-3)
    Details
    Publikationsdatum: 1950
    Schlagwort(e): Seismology ; D" ; density ; Earth model, also for more shallow analyses !
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 6
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    Unbekannt
    Revised travel time curves for Southern California (1950)
    In:  Bull. Geol. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 61, no. 6, pp. 1546, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1950
    Schlagwort(e): Travel time ; Seismology
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 7
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    Larger shocks of 1949 (1950)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1949, no. 6, pp. 72, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1950
    Schlagwort(e): Earthquake catalog ; Seismology ; Seismicity
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 8
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    Unbekannt
    The T phase of shallow-focus earthquakes (1950)
    In:  Bull. Seism. Soc. Am., Warszawa, EGS, vol. 40, no. 5, pp. 25-51, pp. B05S16, (ISSN: 1340-4202)
    Details
    Publikationsdatum: 1950
    Schlagwort(e): Seismology ; T phase ; Nuclear explosion ; BSSA
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 9
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    Unbekannt
    Über die Wirkung des Rapserdfloh-Larvenbefalls auf die Rapspflanze (1950)
    In:  Mitteilungen aus der Biologischen Zentralanstalt für Land- und Forstwirtschaft, Berlin-Dahlem, Heft 69
    Details
    Publikationsdatum: 1950
    Beschreibung: Bericht über die Ergebnisse der Untersuchungen zu den Wechselwirkungen zwischen Larve und Wirtspflanze KATASTER-BESCHREIBUNG: Einfluss der Temperatur auf den Larvenbefall KATASTER-DETAIL: Delta T -, dann Entwicklungsdauer der Larven +; T 〉 0°C, dann Froststarre und Wanderfähigkeit -; Delta T - und Delta Relf +, dann Larvenmortalität +
    Schlagwort(e): Berlin-Dahlem ; 1948-1949 ; Insekten ; Luftfeuchte ; Pflanzenschädling ; Temperatur ; Raps
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 10
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    Unbekannt
    Über die Frühjahrsentwicklung der grünen Pfirsichblattlaus (Myzodes persicae Sulzer) am Primärwirt im Hinblick auf ihre Bedeutung als Virusüberträger im Kartoffelfeld (1950)
    In:  Z. Pflanzenkrankheiten (Pflanzenpathol.) Pflanzenschutz, p. 351-357
    Details
    Publikationsdatum: 1950
    Beschreibung: Untersuchungen zur Schlüpfzeit, der Generationszahl und der Abflugzeiten von Myzodes persicae Sulzer am Pfirsichbaum KATASTER-BESCHREIBUNG: Zusammenhang zwischen Klima, Witterung und Schlüpfablauf von Myzodes persicae KATASTER-DETAIL: Delta T -, dann Verzögerung im Schlüpfablauf
    Schlagwort(e): Bonn ; 1947-1950 ; Kartoffeln ; Pflanzenschädling ; Temperatur
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 11
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    Unbekannt
    Untersuchungen über die Möhrenfliege (Psila rosae F.) in Schleswig-Holstein (1950)
    In:  Nachrichtenblatt des Deutschen Pflanzenschutzdienstes, p. 171-172
    Details
    Publikationsdatum: 1950
    Beschreibung: Bericht über die Beobachtungen zur Entwicklung und zum Auftreten der Möhrenfliege unter dem Einfluss der Witterung und der Lage KATASTER-BESCHREIBUNG: Einfluss der Witterung und der Lage auf die Befallsstärke der Fliege KATASTER-DETAIL: Delta Lichtintensität +, dann Möhrenfliegenbefall -; Delta Nied +, dann Entwicklung der Maden +; Delta Wind +, dann Befall -
    Schlagwort(e): Schleswig-Holstein ; 1948-1949 ; Insekten ; Niederschlag ; Pflanzenschädling ; Temperatur ; Trockenheit ; Wind ; Witterung ; Sonnenscheindauer ; Gemüse
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 12
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    Witterung, Wasserbilanz und Ertragsschwankungen von Feldkulturen (1950)
    In:  Archiv der wiss. Ges. f. Land- und Forstwirtschaft 2
    Details
    Publikationsdatum: 1950
    Beschreibung: Untersuchungen zu Ertragsunterschieden bei Zuckerrüben, Kartoffeln und Hafer durch Errechnen der Wasserbilanz in einzelnen Monaten KATASTER-BESCHREIBUNG: Einfluss von Temperatur und Niederschlag (=der Wasserbilanz) auf den Ertrag von Zuckerrübe, Hafer und Kartoffel KATASTER-DETAIL: Wasserbilanz (März bis April) ausgeglichen oder leicht positiv, dann Erträge +; Wasserbilanz (Mai bis Juni) stark negativ über mindestens 25 Tage, dann Erträge +; Wasserbilanz (Juli bis September) ausgeglichen, dann Erträge +; Delta T (Frühjahr) +, dann Erträge +; Delta T +, dann Erträge (Zuckerrübe) +; Delta T (außer Juli; bes. Juni) -, dann Erträge (Hafer)+
    Schlagwort(e): Niedersachsen, Grossraum Hannover - Göttingen ; 1932-40, 1947-49 ; Kartoffeln ; Ertrag ; Hafer ; Landwirtschaft ; Niederschlag ; Temperatur ; Trockenheit ; Verdunstung ; Wassermangel
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 13
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    Über Beziehungen zwischen Witterungsverlauf und Ertragsleistung bei landwirtschaftlichen Kulturpflanzen im Land Brandenburg, 2. Beitrag: Sommer- und Wintergetreide (1950)
    In:  Zeitschrift für Acker- und Pflanzenbau 92:100-124.
    Details
    Publikationsdatum: 1950
    Beschreibung: Einteilung der Witterung in Pentaden, Berechnung einer Wetterwertzahl und Bezug zum Ernteertrag KATASTER-BESCHREIBUNG: Einfluss der Witterung (Niederschlag, Temperatur) auf den Ertrag verschiedener Getreidearten (Sommerweizen, Sommergerste, Sommerroggen, Hafer, Winterweizen, Wintergerste, Winterroggen) KATASTER-DETAIL: Delta Tmit (Pentade) 〉 5°C, dann Beginn Vegetationsperiode; Delta Nied (Winter) -, dann Ertrag (Sommergetreidearten) +; Delta Nied (März) -, dann Erträge (Sommerweizen, Sommergerste) +; Delta Nied (Winter) +, dann Erträge (Wintergetreidearten) -; Delta Nied (Winter) -, dann Erträge (Winterweizen, Wintergerste) -; t (T 〉 5°C) + (früher), dann Erträge (Winterweizen, Wintergerste) +; Detaillierte Informationen zu den einzelnen Getreidearten: siehe Artikel
    Schlagwort(e): Brandenburg ; 1938-39, 1943 ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Weizen ; Wind ; Witterung ; Hackfrüchte
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 14
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    Unbekannt
    Die Zunahme wichtiger Getreideschädlinge als Folge der besonderen Witterungserscheinungen in den letzten Jahren (1950)
    In:  Pflanzenschutz, Jahrgang 2, Nr. 8, p. 95-97
    Details
    Publikationsdatum: 1950
    Beschreibung: Beobachtungen zum Auftreten von Roggengallmücke, Halmfliege, Getreidehalmwespe, Hafermilbe und Zwergzikade unter bestimmten Witterungsbedingungen (warme und trockene Sommer und Herbste) KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur und Niederschlag) im Sommer und Herbst auf das Auftreten der Getreideschädlinge KATASTER-DETAIL: Delta T (Sommer und Herbst) + und Delta Nied (Sommer und Hebrst) -, dann Auftreten +; Trockenperioden über mindestens 2 Jahre, dann Massenauftreten
    Schlagwort(e): Bayern ; 1947-1950 ; Anbautermine ; Landwirtschaft ; Niederschlag ; Pflanzenschädling ; Roggen ; Temperatur ; Trockenheit ; Weizen ; Witterung
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 15
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    An Analysis of the Applicability of the Hypersonic Similarity Law to the Study of Flow About Bodies of Revolution at Zero Angle of Attack (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The hypersonic similarity law as derived by Tsien has been investigated by comparing the pressure distributions along bodies of revolution at zero angle of attack. In making these comparisons, particular attention was given to determining the limits of Mach number and fineness ratio for which the similarity law applies. For the purpose of this investigation, pressure distributions determined by the method of characteristics for ogive cylinders for values of Mach numbers and fineness ratios varying from 1.5 to 12 were compared. Pressures on various cones and on cone cylinders were also compared in this study. The pressure distributions presented demonstrate that the hypersonic similarity law is applicable over a wider range of values of Mach numbers and fineness ratios than might be expected from the assumptions made in the derivation. This is significant since within the range of applicability of the law a single pressure distribution exists for all similarly shaped bodies for which the ratio of free-stream Mach number to fineness ratio is constant. Charts are presented for rapid determination of pressure distributions over ogive cylinders for any combination of Mach number and fineness ratio within defined limits.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-2250
    Format: application/pdf
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  • 16
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    An Approximate Method of Calculating Pressures in the Tip Region of a Rectangular Wing of Circular-Arc Section at Supersonic Speeds (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-2211
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 17
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    Large-Scale Flight Measurements of Zero-Lift Drag at Mach Numbers from 0.90 to 1.95 of 1/14-Scale Model of the Northrop MX-775B Pilotless Aircraft with Small Body (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: A flight test was made a t high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a 1/14-scale model of the Northrop MX-775B pilotless aircraft with small small body. The triangular wing of the model had 67.5 deg leading-edge sweep and 15 deg. trailing-edge sweep, The wing airfoil sections were modified NACA 0004 sections. The drag coefficient based on total wing area was 0.0107 at Mach number 1.60. At transonic speeds the maximum drag coefficient was 0.0125. The force-break Mach number was 0,98.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL50H18
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    Tests of a Hermes A-2 Missile Body at Mach Number 4.04 (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Force tests on a proposed body shape of the Hermes A-2 missile with and without longitudinal spoilers were made at Mach number 4.04. Values of normal force coefficient, pitching-moment coefficient, and center-of-pressure position were obtained.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL50H23A
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 19
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    Free-Spinning-Tunnel Investigation of a 1/24-Scale Model of the Grumman AF-2S, -2W Airplane (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation of the spin and recovery characteristics of a 1/24-scale model of the Grumman AF-2S, -2W airplane was conducted in the Langley 20-foot free-spinning tunnel. The effects of controls on the erect and inverted spin and recovery characteristics for a range of possible loadings of the.airplane were determined. The effect of a revised-tail installation (small dual fins added to the stabilizer of the original tail and the vertical-tail height of the original tail increased) and the effect of various ventral-fin and antispin-fillet installations were determined. The investigation also included spin-recovery parachute tests.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL51B20
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 20
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    Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds Several Combinations of the Tail with Each of Two Foreshortened Body Segments (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL50G13
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 21
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    Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF1OF-1 Airplane (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/30 - scale model of the Grumman XFlOF-1 airplane to determine its spin and recovery characteristics. The investigation included erect and inverted spins for both the straight-wing and swept-wing configurations. Tests to determine the optimum size spin-recovery parachutes and the rudder forces required for recovery were also made. The results indicated that in the straight-wing configuration, satisfactory recoveries of the airplane will be obtained from erect and inverted spins by rudder reversal alone. In the swept-wing configuration recoveries will be unsatisfactory from erect spins. Unsweeping the wings during the spin and reversal of the rudder, however, will lead to eventual recovery. The test results also indicated that, if existing small ailerons are made deflectable through large angles, satisfactory recoveries will be obtained from erect spins in the swept-wing configuration by simultaneous movement of the rudder to against the spin and movement of the ailerons to with the spin. Normal-size ailerons deflected through a normal range would also be effective. Satisfactory recoveries by rudder reversal will be obtained from inverted spins in the swept-wing configuration. In the straight-wing configuration a 14.2-foot tail parachute or a 5.0-foot wing-tip parachute opened on the outer wing tip will effect satisfactory recovery of the airplane by parachute action alone; a 30.0-foot tail parachute or a 10.0-foot wing-tip parachute will be required for the swept-wing configuration. The forces required to fully reverse the rudder should be within the capabilities of the pilot.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL50L14
    Format: application/pdf
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  • 22
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    Dynamic Response of Control Servo System Installed in NAES-Equipped SB2C-5 Airplane (BuAer No. 83135) (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Dynamic--response measurements for various conditions of displacement and rate signal input, sensitivity setting, and simulated hinge moment were made of the three control-surface servo systems of an NAES-equipped remote-controlled airplane while on the ground. The basic components of the servo systems are those of the General Electric Company type G-1 autopilot using electrical signal. sources, solenoid-operated valves, and hydraulic pistons. The test procedures and difficulties are discussed, Both frequency and transient-response data, are presented and comparisons are made. The constants describing the servo system, the undamped natural frequency, and the damping ratio, are determined by several methods. The response of the system with the addition of airframe rate signal is calculated. The transfer function of the elevator surface, linkage, and cable system is obtained. The agreement between various methods of measurement and calculation is considered very good. The data are complete enough and in such form that they may be used directly with the frequency-response data of an airplane to predict the stability of the autopilot-airplane combination.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SA50J05
    Format: application/pdf
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  • 23
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    Preliminary Performance Data on Westinghouse Electronic Power Regulator Operating on J34-WE-32 Turbojet Engine in Altitude Wind Tunnel (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: The behavior of the Westinghouse electronic power regulator operating on a J34-WE-32 turbojet engine was investigated in the NACA Lewis altitude wind tunnel at the request of the Bureau of Aeronautics, Department of the Navy. The object of the program was to determine the, steady-state stability and transient characteristics of the engine under control at various altitudes and ram pressure ratios, without afterburning. Recordings of the response of the following parameters to step changes in power lever position throughout the available operating range of the engine were obtained; ram pressure ratio, compressor-discharge pressure, exhaust-nozzle area, engine speed, turbine-outlet temperature, fuel-valve position, jet thrust, air flow, turbine-discharge pressure, fuel flow, throttle position, and boost-pump pressure. Representative preliminary data showing the actual time response of these variables are presented. These data are presented in the form of reproductions of oscillographic traces.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SE50J11
    Format: application/pdf
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  • 24
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    An Investigation of the Longitudinal Characteristics of the MX-656 Configuration Using Rocket-Propelled Models Preliminary Results at Mach Numbers from 0.65 to 1.25 (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: A rocket-propelled model of the Mx-656 configuration has been flown through the Mach number range from 0.65 to 1.25. An analysis of the response of the model to rapid deflections of the horizontal tail gave information on the lift, drag, longitudinal stability and control, and longitudinal-trim change. The lift-coefficient range covered by the test was from -0.2 to 0,3 throughout most of the Mach number range, The model was statically and dynamically stable throughout the lift-coefficient and Mach number range of the test. At subsonic speeds the aerodynamic center moved f o m r d with increasing lift coefficient. The most forward position of the aerodynamic center was about 12,5 percent of the mean aerodynamic chord at a small positive lift coefficient and at a Mach number of about 0.84. A t supersonic speeds the aerodynamic center was well aft, varying from 33 to 39 percent of the mean aerodynamic chord at Mach numbers of 1.0 and 1.25, respectively. Transonic-trim change, as measured by the change in trim lift coefficient with Mach number at a constant t a i l setting, was of small magnitude (about 0.1 lift coefficient for zero tail setting). The zero-lift/drag coefficient increased about 0.042 in the region between a Mach number of 0.9 and 1.1
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL50J03
    Format: application/pdf
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  • 25
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    Investigation of the Model ME 210 in the Spin Wind Tunnel of the DVL (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: After conclusion of the spin investigation of the model Me 210 with elongated fuselage and central vertical tail surfaces (model condition III; reference 3), tests were performed on the same model with a vee tail (model condition IV). Here the entire tail surfaces consist of only one surface with pronounced dihedral. Since the blanketing of the vertical tail surfaces by the horizontal tail surfaces, which may occur in case of standard tail surfaces, does not occur here, one could expect for this type of tail surface favorable spin characteristics, particularly with respect to rudder effectiveness for spin recovery. However, the test results did not confirm these expectations. The steady spin was shown to be very irregular; regarding rudder effectiveness the vee tail surfaces proved to be inferior even to standard tail surfaces, thus they represent the most unfavorable of the four fuselage and tail-surface combinations investigated so far.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1222 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters (ZWB) Untersuchungen und Mitteilungen; Rept-1288
    Format: application/pdf
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  • 26
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    Mechanism of faulting in Southern California indicated by seismograms (1941)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 31, no. 6, pp. 263-302, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1941
    Schlagwort(e): Tectonics ; Seismicity ; Seismology ; BSSA
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 27
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    Notes of interest (roots of mountains) (1941)
    In:  Earthquake Notes, Milano, Gustav Fischer, vol. 13, no. 6, pp. 4, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1941
    Schlagwort(e): Seismology ; Gravimetry, Gravitation
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 28
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    Unbekannt
    Seismology (1941)
    Geological Society of America
    In:  Professional Paper, Geology 1888-1938, 50th Anniversary Volume, New York, Geological Society of America, vol. 3, no. VIIa, pp. 438-470, (ISBN: 3-540-23712-7)
    Details
    Publikationsdatum: 1941
    Schlagwort(e): Review article ; Seismology
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 29
    facet.materialart.
    Unbekannt
    Mechanism of faulting in Southern California indicated by seismograms (1941)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 52, no. 6, pp. 1950, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1941
    Schlagwort(e): Tectonics ; Seismicity ; Seismology
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 30
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    Unbekannt
    Die Übervermehrung von Diprion pini L. im westslowakischen Kieferngebiet (1941)
    In:  Ztschr. Pfl.krankh. 51: 257-278
    Details
    Publikationsdatum: 1941
    Beschreibung: Beschreibung der Massenvermehrung der Kiefernblattwespe, Hauptgrung ist die Umwandlung von ursprünglich Laubwaldgesellschaften in reine Kieferngesellschaften, Bedeutung der Temperatur für das Überliegen der Larven KATASTER-BESCHREIBUNG: Temperatur und Luftfeuchte für das Überliegen der Larven entscheidend und damit auch für ein Massenauftreten im darauffolgenden Jahr, Begünstigung der Parasitierung der Kieferblattwespe KATASTER-DETAIL: Delta T- (Juli-August und im Winter), dann Geschlechterfolge von Diprion pini stark dezimiert
    Schlagwort(e): Slowakei ; 1939-40 ; Insekten ; Luftfeuchte ; Kiefer ; Pflanzenschädling ; Temperatur ; Parasit
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 31
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    Massenvermehrung forstlicher Schadinsekten (1941)
    In:  Dtsch. Forstztg. 10: 307-308
    Details
    Publikationsdatum: 1941
    Beschreibung: Beschreibung der großen Frassschäden der letzten Jahrzehnte, bezug der Temperatur und des Niederschlages auf die Entwicklungsmöglichkeit einer Population KATASTER-BESCHREIBUNG: Ziiterte Untersuchungen zur Entwicklung der Nonnenraupe KATASTER-DETAIL: Delta T+ (Temperaturoptimum von 21.5°C, Ende April-Anfang Mai), dann günstige Entwiclungsbedingungen Delta Nied- (relative Feuchte schwankt zwischen 50-100%), dann Absterben großer Zahl futtersuchender Raupen
    Schlagwort(e): Deutschland, teilw. einzelne Regionen ; 1850-1940 ; Insekten ; Luftfeuchte ; Fichte ; Forst ; Kiefer ; Niederschlag ; Pflanzenschädling ; Temperatur
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 32
    facet.materialart.
    Unbekannt
    Seismicity of the earth (1941)
    Geol. Soc. Am.
    In:  New York, 7 + 131 pp., Geol. Soc. Am., vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publikationsdatum: 1941
    Schlagwort(e): Seismology ; Seismicity ; Review article
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 33
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    Unbekannt
    A contribution to the seismic history of Missouri (1941)
    In:  Bull. Seism. Soc. Am., Oxford and Edinburgh, Blackwell Scientific Publications, vol. 31, no. 19, pp. 187-224, pp. 1484, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1941
    Schlagwort(e): Seismology ; Seismicity ; BSSA
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 34
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    Notes on the Stability and Control of Tailless Airplanes (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Problems involved in the stability and control of tailless airplanes are discussed. Such factors as the location of the aerodynamic center and its effect on the longitudinal stability, longitudinal trim with high-lift devices, the effects of various changes in the shape of the wing on lateral stability, and the effects of nacelles are covered. It appears that sufficient stability and controllability can be secured without sweepback. With sweepback, a flap over the center section of the wing may be used to serve the dual purpose of elevator control and high-lift device. Sweepback introduces undesirable stalling characteristics, however, and may require auxiliary devices to prevent stalling of the tips.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-837
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 35
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    The Selection of Propellers for High Thrust at Low Airspeed (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Problem of improving thrust at low speeds is primarily one of reducing angle of attack of operation of sections to improve L/D or reducing blade helix angle. An analysis, based on recent propeller data, is presented for determining improvements in thrust or efficiency which could be obtained by increased number of blades, increased blade width, increased diameter, dual rotation, and two-speed gearing. All methods were found very effective, particularly two-speed gearing.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-483
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 36
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    Flight Investigation of Wing-gun Fairings on a Fighter Type Airplane (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Description is given of flight tests conducted on gun fairings, designed to correct the detrimental effects of the projecting and submerged wing guns on an F4F-3 fighter. It was found that the installation of unfaired guns on a clean wing resulted in a premature stall that increased the stalling speed in the carrier-approach and landing conditions of flight by suitably fairing the guns, it was possible to reduce the stalling speeds to values approaching very nearly the clean-wing values.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-247
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 37
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    Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-493
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 38
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    Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces. The results showed that the vee-type tail tested, with a dihedral angle of 35.3 deg, was about 71 percent as effective in pitch as the conventional tail and had a yawing-moment to pitching-moment ratio of 0.3. The conventional tail, the panels of which were all congruent to those of the vee-type tail, had a yawing-moment to pitching-moment ratio of 0.48. These ratios are in fair agreement with values calculated by methods shown in this and previous reports. The values of the measured moments were reduced from 15 to 25 percent of the calculated value by fuselage interference.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-815
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 39
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    Wind-tunnel Tests of Eight-blade Single and Dual-rotating Propellers in the Tractor Position (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Tests of 10-ft. diameter, eight-blade, single - and dual - rotating propellers were conducted in 20-ft propeller research tunnel. Propellers were mounted at front end of a streamline body in spinners that covered hubs and parts of shanks. Effect of a symmetrical wing mounted in slipstream was investigated. Blade-angle settings ranged from 20 Degrees to 65 Degrees. Results indicated that dual rotation resulted in gains of from 1 to 8 percent in efficiency over single rotation for eight-blade propellers, but presence of a wing reduced gain about one-half. Greater power absorption caused by dual rotation over flight range and higher efficiency or thrust for range of take-off and climb was indicated
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-384
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 40
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    Development of Cowling for Long-nose Air-cooled Engine in the NACA Full-scale Wind Tunnel (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation of cowlings for long-nose radial engines was made on the Curtiss XP-42 fighter in the NACA full-scale wind tunnel. The unsatisfactory aerodynamic characteristics of all the cowlings with scoop inlets tested led to the development of the annular high-velocity inlet cowlings. Tests showed that ratio of cooling-air velocity at cowling inlet to stream velocity should not be less than 0.5 for this type of cowling and that critical compressibility speed can be extended to more than 500 mph at 20,000 ft altitude.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-241
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 41
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    Progress Report on Cowlings for Air-Cooled Engines Investigated in the NACA 19-Foot Pressure Wind Tunnel (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: At the present time there is considerable demand for improvement in the aerodynamic characteristics of cowlings for radial air-cooled aircraft engines. During the past year, numerous cowling arrangements have been investigated in various departments of the NACA laboratory. Although a few full-scale investigation have been carried out, most of the studies have been preliminary in nature and have been confined to the investigation of model arrangement in wind tunnels. Because of the existing national emergency it appears advisable to release immediately to the aircraft industry the information available on the more promising of the arrangements that have been studied. An investigation having as its aim the improvement in performance and flying qualities of single-engine air-cooled military pursuit airplanes is being conducted in the NACA 10-foot pressure wind tunnel. As a part of that investigation, studies have been made of the relative merits of a conventional NACA open-nose cowling arrangement and of a less conventional but better streamline NACA high-speed cowling arrangement in which the cooling air enters the cowling through an opening ahead of the propeller, passes internally through an element of the cowling which rotates with the propeller, and thence past the engine cylinders to the exit at the rear of the engine. These investigations indicate that at airplane speeds of around 400 miles per hour there is not a great deal to be gained in high-speed performance through the application of the latter cowling arrangement, but at speeds in excess of about 450 miles per hour a very appreciable gain is indicated. Present indications are that improved engine cooling can be obtained throughout the speed range as well as ground cooling through the use of the high-speed cowling. This paper summarizes the results obtained from wind-tunnel tests of models of the two cowling arrangements.
    Schlagwort(e): Aerodynamics
    Materialart: HQ-E-DAA-TN59228
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 42
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    Wind-Tunnel Investigation of an NACA Low-Drag Tapered Wing with Straight Trailing Edge and Simple Split Flaps, Special Report (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation was conducted in the NACA 19-foot pressure wind tunnel of a tapered wing with straight railing edge having NACA 66 series low-drag airfoil sections and equipped with full-span and partial-span simple split flaps. The airfoil sections used were the NACA 66,2-116 at the root and the 66,2-216 at the tip. The primary purpose of the investigation was to determine the effect of the split flaps on the aerodynamic characteristics of the tapered wing. Complete lift, drag, and pitching-moment coefficients were determined for the plain wing and for each flap arrangement through a Reynold number range of 2,600,000 to 4,600,000. The results of this investigation indicate that values of maximum lift coefficient comparable to values obtained on tapered wings with conventional sections and similar flap installations can be obtained from wings with the NACA low-drag sections. The increment of maximum lift due to the split flap was found to vary somewhat with Reynold number over the range investigated. The C(sub L)max of the wing alone is 1.49 at a Reynolds number of 4,600,000; whereas with the partial-span simple split flap it is 2.22 and with the full-span arrangement, 2.80. Observations of wool tufts on the wing indicate that the addition of split flaps did not appreciable alter the pattern of the stall; even though the stall did occur more abruptly than with the wing alone.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-ACR-212 , NACA-SR-212
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 43
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    Wind-Tunnel Investigation of an NACA 66,2-216 Low-Drag Wing with Split Flaps of Various Sizes, Special Report (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation was conducted in the NACA 19-foot pressure wind tunnel of a rectangular wing having NACA 66, 2-216 low-drag airfoil sections and various sizes of simple split flaps. The purpose of the investigation was, primarily, to determine the influence of these flap installations on the aerodynamic characteristics of the wing. Complete lift, drag, and pitching-moment characteristics were determined for a range of test Reynolds numbers from about 2,600,000 to 4,600,000 for each of the installations and for the plain wing. The results of this investigation indicate that values of maximum lift coefficient similar to those of wings with conventional airfoil sections and split flaps can be expected of wings having the NACA 66,2-216 low-drag sections. The increment of maximum lift due to the split flap was found to be practically independent of the Reynolds number over the range investigated. The optimum split flap on the basis of maximum lift appears to have a chord about 20% of the wing chord and a deflection of 60 degrees. The C(sub L) max of the wing with the 0.20c partial-span flap deflected 60 degrees is 2.07 at a Reynolds number of 4,600,000 while with the full-span flap it is approximately 2.53; the increment of the maximum lift coefficient due to the flap is approximately proportional to the flap span. Although the addition of a split flap tends to hasten the stall and to cause it to occur more abruptly, little change in pattern is evidenced by observations of the behavior of wool tufts on the wing.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-SR-208
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 44
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    The Effect of Various Wing-Gun Installations on the Aerodynamic Characteristics of an Airplane Model Equipped with an NACA Low-Drag Wing, Special Report (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation was made in the NACA 19-foot pressure wind tunnel to determine the effect of various win-gun installation on the aerodynamic characteristics of a model with an NACA low-drag wing. Measurements were made of lift and drag over an angle-of-attack range and for several values of dynamic pressure on a four-tenths scale model of a high-speed airplane equipped with the low-drag wing and with various wing-gun installations. Two installations were tested: one in which the blast tube and part of the gun barrel protrude ahead of the wing and another in which the guns is mounted wholly within the wing. Two types of openings for the latter installation were tested. For each installation three simulated guns were mounted in each wing. The results are given in the form of nondimensional coefficients. The installations tested appear to have little effect on the maximum-lift coefficient of the model. However, the drag coefficient shows a definite change. The least adverse effect was obtained with the completely internal mounting and small nose entrance. The results indicate that a properly designed wing-gun installation will have very little adverse effect on the aerodynamic characteristics of the low-drag wing.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-SR-198
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 45
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    Tests of Wing Machine-Gun and Cannon Installations in the NACA Full-Scale Wind Tunnel, Special Report (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: At the request of the Bureau of Aeronautics, an investigation was conducted in the full-scale wind tunnel of wing installations of .50-caliber machine guns and 20-millimeter cannons. The tests were made to determine the effect of various gun installations on the maximum lift and the high-speed drag of the airplane.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-SR-205
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 46
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    Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps (1941)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord spit flaps, deflected 60 deg span ratios of 0.3, 0.5, 0.7 and 1.0 respectively. In order to get data from which to calculate the characteristics of the flapped wing, the investigation was extended to include tests of the four rectangular airfoils of the NACA 4400R series (4409R, 4412R, 4415R, and 4418R) with full-span 0.2 chord, trailing edge split flaps deflected 60 deg.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-SR-171
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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