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  • Other Sources  (267)
  • Aerodynamics  (146)
  • Aircraft Stability and Control  (77)
  • Cell & Developmental Biology
  • General Chemistry
  • Limnology
  • Pflanzenschädling
  • Seismicity
  • 2020-2024  (2)
  • 1945-1949  (257)
  • 1920-1924
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  • 1
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    Seiscloud, a tool for density-based seismicity clustering and visualization (2020)
    Springer Netherlands
    Details
    Publication Date: 2023-06-09
    Description: Clustering algorithms can be applied to seismic catalogs to automatically classify earthquakes upon the similarity of their attributes, in order to extract information on seismicity processes and faulting patterns out of large seismic datasets. We describe here a Python open-source software for density-based clustering of seismicity named seiscloud, based on the pyrocko library for seismology. Seiscloud is a tool to dig data out of large local, regional, or global seismic catalogs and to automatically recognize seismicity clusters, characterized by similar features, such as epicentral or hypocentral locations, origin times, focal mechanisms, or moment tensors. Alternatively, the code can rely on user-provided distance matrices to identify clusters of events sharing indirect features, such as similar waveforms. The code can either process local seismic catalogs or download selected subsets of seismic catalogs, accessing different global seismicity catalog providers, perform the seismic clustering over different steps in a flexible, easily adaptable approach, and provide results in form of declustered seismic catalogs and a number of illustrative figures. Here, the algorithm usage is explained and discussed through an application to Northern Chile seismicity.
    Description: Helmholtz-Zentrum Potsdam Deutsches GeoForschungsZentrum - GFZ (4217)
    Keywords: ddc:551.22 ; Seismicity ; Clustering ; Location ; Moment tensor
    Language: English
    Type: doc-type:article
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    CITATION GEO-LEO
  • 2
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    Seismicity in the Northern Rhine Area (1995–2018) (2020)
    Springer Netherlands
    Details
    Publication Date: 2023-06-09
    Description: Since the mid-1990s, the local seismic network of the University of Cologne has produced digital seismograms. The data all underwent a daily routine processing. For this study, we re-processed data of almost a quarter century of seismicity in the Northern Rhine Area (NRA), including the Lower Rhine Embayment (LRE) and the Eifel Mountain region (EMR). This effort included refined discrimination between tectonic earthquakes, mine-induced events, and quarry blasts. While routine processing comprised the determination of local magnitude ML, in the course of this study, source spectra-based estimates for moment magnitude MW for 1332 earthquakes were calculated. The resulting relation between ML and MW agrees well with the theory of an ML ∝ 1.5 MW dependency at magnitudes below 3. By applying Gutenberg-Richter relation, the b-value for ML was less (0.82) than MW (1.03). Fault plane solutions for 66 earthquakes confirm the previously published N118° E direction of maximum horizontal stress in the NRA. Comparison of the seismicity with recently published Global Positioning System–based deformation data of the crust shows that the largest seismic activity during the observation period in the LRE occurred in the region with the highest dilatation rates. The stress directions agree well with the trend of major faults, and declining seismicity from south to north correlates with decreasing strain rates. In the EMR, earthquakes concentrate at the fringes of the area with corresponding the largest uplift.
    Description: Projekt DEAL
    Keywords: ddc:551.22 ; Northern Rhine Area ; Lower Rhine Embayment ; Eifel ; Seismicity ; Moment magnitude ; Crustal deformation
    Language: English
    Type: doc-type:article
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    CITATION GEO-LEO
  • 3
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    Larger shocks of 1948 (1949)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1948, no. 6, pp. 129, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1949
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Earthquake study in Southern California 1948 (1949)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 30, no. 6, pp. 595-597, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    In case of earthquake disaster (1949)
    American Red Cross, 2 pp.
    In:  Princeton, New Jersey, 7 + 273 pp., 1. ed., American Red Cross, 2 pp., vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; Earthquake precursor: prediction research
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Bemerkenswerte Schädlingsmeldungen (IV) (1949)
    In:  Ztschr. hyg. Zool. 37; p.317-320
    Details
    Publication Date: 1949
    Description: Bericht über das Auftreten einiger Vorrats- und Holzschädlinge in Haushalten aus den Jahren 1947-1949. In sehr geringem Umfang ist auch Zahlenmaterial angegeben. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Baden-Württemberg ; 1947-1949 ; Forst ; Pflanzenschädling
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    BIBLIOGRAPHY INKA BB
  • 7
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    Der Einfluß von Tageszeiten und Witterung auf Ausschlüpfen, Begattung und Eiablage des Springwurmwicklers Sparganothis pilleriana Schiff (1949)
    In:  Z. angew. Entom. 31; p.261-274
    Details
    Publication Date: 1949
    Description: Der Autor untersuchte im Freiland die Zeiten zu denen Ausschlüpfen, Begattung und Eiablage des Springwurmwicklers stattfindet. Zudem wurden Temperatur und relative Luftfeuchte gemessen und mit den Beobachtungen zum Schaderreger in Verbindung gesetzt. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Breisgau, Freiburg ; 1943-1944 ; Luftfeuchte ; Pflanzenschädling ; Temperatur ; Wein
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    BIBLIOGRAPHY INKA BB
  • 8
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    Frittfliegenbefall in den Ähren der Wintergerste (1949)
    In:  Neue Mitt. Landwirtsch. 4; p.130-132
    Details
    Publication Date: 1949
    Description: Der Autor beschreibt den Lebenszyklus der Frittfliege und dokumentiert das Auftreten des Schädlings in vergangenen Jahren. In einem sehr kurzen Absatz wird das Auftreten des schädlings mit warmem Frühlingswetter und der Sonnenscheindauer bzw. der Temperatur im Mai in Verbindung gebracht. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1948 ; Getreide ; Pflanzenschädling ; Gerste
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    BIBLIOGRAPHY INKA BB
  • 9
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    Beobachtungen über das Auftreten der Pfirsichblattlaus in Nordbaden während der beiden Extremjahre 1947 und 1948 im Zusammenhang mit der Frage des Kartoffelabbaues (1949)
    In:  Nachr.-Bl. Biol. Ztr.-Anst. Braunschweig, p. 72-73
    Details
    Publication Date: 1949
    Description: Untersuchungen zum Auftreten der Pfirsichblattlaus und zum Befall mit der Blattrollkrankheit KATASTER-BESCHREIBUNG: Abhängigkeit der Stärke des Pfirsichblattlausauftretens vom Niederschlag im Mai/Juni KATASTER-DETAIL: Delta Nied: Nied 〉 80mm, dann Laus -
    Keywords: Baden ; 1947 - 1948 ; Kartoffeln ; Niederschlag ; Pflanzenschädling
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    BIBLIOGRAPHY INKA BB
  • 10
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    Zur Biologie und Bekämpfung des Pflaumenwicklers (Laspeyresia funebrana Tr.) in Norddeutschland (1949)
    In:  Anz. Schädlingskunde, p. 40-43
    Details
    Publication Date: 1949
    Description: Beschreibende Beobachtungen zu den Generationen und zur Eiablage des Pflaumenwicklers sowie zur Bekämpfung mittels Spritzungen KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Keywords: Norddeutschland ; 1938/39 u. 1945-1947 ; Pflanzenschädling
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    BIBLIOGRAPHY INKA BB
  • 11
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    Wie überwintert die grüne Pfirsichblattlaus? (1949)
    In:  Neue Mitt. Landwirtsch. 4; p.153-154
    Details
    Publication Date: 1949
    Description: Autor präsentiert Beobachtungsergebnisse, sowie Ergebnisse von Laborversuchen zum Überwintern der grünen Pfirsichblattlaus. Untersucht wurde hauptsächlich das untere Temperaturlimit für den Schädling. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Labor ; 1943-1948 ; Pflanzenschädling ; Obst
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    BIBLIOGRAPHY INKA BB
  • 12
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    Überwinterung der Pfirsichblattlaus (Myzodes persicae) im Winter 1948/1949 (1949)
    In:  Nachr.-Bl. Biol. Ztr.-Anstalt Braunschweig, p. 82
    Details
    Publication Date: 1949
    Description: Verbale Beobachtungen zur Freilandüberwinterung der grünen Pfirsichblattlaus KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Keywords: Niedersachsen ; 1948-1949 ; Pflanzenschädling
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    BIBLIOGRAPHY INKA BB
  • 13
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    Ein Auftreten des Zuckerrübenrüsslers (Tanymecus palliatus F.) an Spinat (1949)
    In:  Nachr. Bl. Biolog. Ztr.-Anst. Braunschweig, p.19
    Details
    Publication Date: 1949
    Description: Verbale Beschreibung des Massenauftretens 1948 sowie früheren Massenauftretens (1891, 1922, 1925, 1938 und 1939) KATASTER-BESCHREIBUNG: Zusammenhang zwischen Witterung (Temperatur und Luftfeuchte) und dem Massenauftreten des Käfers KATASTER-DETAIL: Delta T + (Sommer und Winter) und Delta Relf (Sommer) -, dann Massenauftreten im Folgejahr
    Keywords: Deutschland ; 1947-1948 ; Zuckerrüben ; Pflanzenschädling ; Temperatur ; Trockenheit ; Witterung ; Gemüse
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    BIBLIOGRAPHY INKA BB
  • 14
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    Seismicity of the earth and associated phenomena (1949)
    Princeton Univ. Press
    In:  Princeton, New Jersey, 7 + 273 pp., 1. ed., Princeton Univ. Press, vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; Textbook of geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 15
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    High Speed Wind-Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 1/16-Scale Model of the D-558-2 Research Airplane at High Subsonic Mach Number and at a Mach Number of 1.2 (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-RM-L9C04
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    NASA TECHNICAL REPORTS
  • 16
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    General Theory of Aerodynamic Instability and the Mechanism of Flutter (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom have been determined. The problem resolves itself into the solution of certain definite integrals, which have been identified as Bessel functions of the first and second kind and of zero and first order. The theory, being based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing-section theory relating to the steady case. The air forces being known, the mechanism of aerodynamic instability has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been arrived at. The solution is of a simple form and is expressed by means of an auxiliary parameter K.
    Keywords: Aerodynamics
    Type: NACA-TR-496
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    NASA TECHNICAL REPORTS
  • 17
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    Boundary Layer Theory (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The purpose of this presentation is to give you a survey of a field of aerodynamics which has for a number of years been attracting an ever growing interest. The subject is the theory of flows with friction, and, within that field, particularly the theory of friction layers, or boundary layers. As you know, a great many considerations of aerodynamics are based on the so-called ideal fluid, that is, the frictionless incompressible fluid. By neglect of compressibility and friction the extensive mathematical theory of the ideal fluid (potential theory) has been made possible.
    Keywords: Aerodynamics
    Type: NACA-TM-1217
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    NASA TECHNICAL REPORTS
  • 18
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    Wind-Tunnel Investigation of the Low-Speed Static Stability and Control Characteristics of a Model of Bell MX-776 (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley stability tunnel to determine the low-speed static stability and control characteristics of a model of the Bell MX-776. The results of the investigation indicated that the basic model configuration was longitudinally stable in the angle-of-attack range from about -16 deg. to 16 deg. but that the stability was a minimum near O deg angle of attack. The data indicated an aerodynamic-center position about 0.64 body diameters behind the center of gravity at low angles of attack. Reduction in the size of the front horizontal fins increased the longitudinal stability. With 20 percent of the span of the normal front horizontal fins cut off the aerodynamic center was about 1.04 body diameters behind the center of gravity, and with front horizontal fins having the same area as the front vertical fins, the aerodynamic center was 2.26 body diameters behind the center of gravity (at low angles of attack).
    Keywords: Aerodynamics
    Type: NACA-RM-SL9G08
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    NASA TECHNICAL REPORTS
  • 19
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    Smooth-Water Landing Stability and Rough-Water Landing and Take-Off Behavior of a 1/13-Scale Model of the Consolidated Vultee Skate 7 Seaplane, TED No. NACA DE 338 (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A model of the Consolidated Vultee Aircraft Corporation Skate 7 seaplane was tested in Langley tank no. 2. Presented without discussion in this paper are landing stability in smooth water, maximum normal accelerations occurring during rough-water landings, and take-off behavior in waves.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9H31
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    NASA TECHNICAL REPORTS
  • 20
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    Rotation in Free Fall of Rectangular Wings of Elongated Shape (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The present report of Mr. Dupleich is the summary of a very extensive experimental study of the well-known mechanical phenomenon: the rotation in free fall (* air, for instance) of more or less elongated rectangles cut out of paper or pasteboard. This phenomenon, the conditions for existence of which depend chiefly on the elongated of the small plate and its weight per unit area, is essentially an aerodynamic phenomenon and as such, raises questions of a certain interest to our department.We believe that the modern concepts of the mechanics of fluids do not have the range attributed to them.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1201 , Scientifiques et Techniques du Secretariat d'Etat a l'Aviation; Rept-178
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    NASA TECHNICAL REPORTS
  • 21
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    Flight Investigations at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Fin-Stabilized Bodies of Revolution having Fineness Ratios of 12.5, 8.91, and 6.04 and Varying Positions of Maximum Diameter (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Rocket-powered models were flown at high-subsonic, transonic, and supersonic speeds to determine the zero-lift drag of fin-stabilized parabolic bodies of revolution differing in fineness ratio and in position of maximum diameter. The present paper presents the results for fineness ratio 12.5, 8.91 and 6.04 bodies having maximum diameters located at stations of 20, 40, 60, and 80 percent of body length. All configurations had cut-off sterns and all had equal base, frontal, and exposed fin areas. For most of the supersonic-speed range models having their maximum diameters at the 60-percent station gave the lowest values of drag coefficient. At supersonic speeds, increasing the fineness ratio generally reduced the drag coefficient for a given position of maximum diameter.
    Keywords: Aerodynamics
    Type: NACA-RM-L9I30
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    NASA TECHNICAL REPORTS
  • 22
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    Spin and Recovery Characteristics of the Northrop XF-89 Airplane (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The spin and recovery characteristics of the Northrop XF-89 airplane, as well as the spin-recovery parachute requirements, the control forces that would be encountered in the spin, and the best method for the crew to attempt an emergency escape are presented in this report. The characteristics were mainly estimated rather than determined by model tests because the XF-89 dimensional and mass characteristics were such as to make this airplane similar to several others, models of which have previously been tested. Brief tests were made on an available model of similar design to augment the estimation. The results indicate that the recovery characteristics will be satisfactory for all airplane loadings if recovery is attempted by use of rudder followed by moving the elevator down. The rudder pedal forces will be within the capabilities of the pilot but the elevator stick forces will be beyond the pilot's capabilities unless a trim tab, or a booster is used. A 9.5-foot-diameter flat-type tail parachute or a 5.0-foot-diameter flat-type wing-tip parachute with a drag coefficient of 0.7 will be a satisfactory emergency spin-recovery device for spin demonstrations and if it is necessary for the crew to abandon the spinning airplane, they should leave from the outboard side of the cockpit.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9B28a
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    NASA TECHNICAL REPORTS
  • 23
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    Preliminary Analysis of Axial-Flow Compressors Having Supersonic Velocity at the Entrance of the Stator (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A supersonic compressor design having supersonic velocity at the entrance of the stator is analyzed on the assumption of two-dimensional flow. The rotor and stator losses assumed in the analysis are based on the results of preliminary supersonic cascade tests. The results of the analysis show that compression ratios per stage of 6 to 10 can be obtained with adiabatic efficiency between 70 and 80 percent. Consideration is also given in the analysis to the starting, stability, and range of efficient performance of this type of compressor. The desirability of employing variable-geometry stators and adjustable inlet guide vanes is indicated. Although either supersonic or subsonic axial component of velocity at the stator entrance can be used, the cascade test results suggest that higher pressure recovery can be obtained if the axial component is supersonic.
    Keywords: Aerodynamics
    Type: NACA-RM-L9G06
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    NASA TECHNICAL REPORTS
  • 24
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    Experimental Flights for Testing of a Reactor as an Expedient for the Termination of Dangerous Spins (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: In the Institute for Flight Mechanics of the DVL a reactor arrangement with a maximum output of 100 kg was investigated as an expedient for the termination of dangerous spins on an airplane of the FW 56 type. reproduce the influence of a disturbance of the steady spin condition by a pitching or yawing moment. The tests were meant to reproduce the influence of a disturbance of the steady spin condition by a pitching and yawing moment.
    Keywords: Aerodynamics
    Type: NACA-TM-1221 , Zentrale fuer Wissenschaftliches Berichtswesen bei der Deutschen Versuchsanstalt fuer Luftfahrt Nr. 1027
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  • 25
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    Systematic model researches on the stability limits of the DVL series of float designs (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: To determine the trim range in which a seaplane can take off without porpoising, stability tests were made of a Plexiglas model, composed of float, wing, and tailplane, which corresponded to a full-size research airplane. The model and full-size stability limits are in good agreement. After all structural parts pertaining to the air frame were removed gradually, the aerodynamic forces replaced by weight forces, and the moment of inertia and position of the center of gravity changed, no marked change of limits of the stable zone was noticeable. The latter, therefore, is for practical purposes affected only by hydrodynamic phenomena. The stability limits of the DVL family of floats were determined by a systematic investigation independent of any particular sea-plane design, thus a seaplane may be designed to give a run free from porpoising.
    Keywords: Aircraft Stability and Control
    Type: NACA/TM-1254
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    NASA TECHNICAL REPORTS
  • 26
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    The Static-Pressure Error of a Wing Airspeed Installation of the McDonnell XF-88 Airplane in Dives to Transonic Speeds (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Measurements were made, in dives to transonic speeds, of the static-pressure position error at a distance of one chord ahead of the McDonnell XF-88 airplane. The airplane incorporates a wing which is swept back 35 deg along the 0.22 chord line and utilizes a 65-series airfoil with a 9-percent-thick section perpendicular to the 0.25-chord line. The section in the stream direction is approximately 8-percent thick. Data up to a Mach number of about 0.97 were obtained within an airplane normal-force-coefficient range from about 0.05 to about 0.68. Data at Mach numbers above about 0.97 were obtained within an airplane normal-force-coefficient range from about 0.05 to about 0.68. Results of the measurements indicate that the static-pressure error, within the accuracy of measurement, is negligible from a Mach number of 0.65 to a Mach number of about 0.97. With a further increase in Mach number, the static-pressure error increases rapidly; at the highest Mach number attained in these tests (about M = 1.038), the error increases to about 8 percent of the impact pressure. Above a Mach number of about 0.975, the recorded Mach number remains substantially constant with increasing true Mach number; the installation is of no value between a Mach number of about 0.975 and at least 1.038, as the true Mach number cannot be obtained from the recorded Mach number in this range. Previously published data have shown that at 0.96 chord ahead of the wing tip of the straight-wing X-l airplanes, a rapid rise of position error started at a Mach number of about 0.8. In the case of the XF-88 airplane, this rise of position error was delayed, presumably by the sweep of the wing, to a Mach number of about 0.97.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9I12
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    NASA TECHNICAL REPORTS
  • 27
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    Wind-Tunnel Investigation of the Low-Speed Static Stability and Control Characteristics of a Model of the Bell MX-776 (RASCAL) in Combined Angle of Attack and Sideslip (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley stability tunnel to determine the low-speed static stability and control characteristics of a model of the Bell MX-776. The results show the model to be longitudinally unstable in the angle-of-attack range around zero angle of attack and to become stable at moderate angles of attack. The results of the present investigation agree reasonably well with results obtained in other facilities at low speed. The present pitching-moment results at low Mach numbers also agree reasonably well with unpublished results of tests of the model at supersonic Mach numbers (up to Mach number 1.86). Unpublished results at moderate and high subsonic speeds, however, indicate considerably greater instability at low angles of attack than is indicated by low-speed results. The results of the present tests also showed that the pitching-moment coefficients for angles of attack up to 12deg remained fairly constant with sideslip angle up to 12deg. The elevators tested produced relatively large pitching moments at zero angle of attack but, as the angle of attack was increased, the elevator effectiveness decreased. The rate of decrease of elevator effectiveness with angle of attack was less for 8deg than for 20deg elevator deflection. Therefore although 8deg deflection caused an appreciable change in longitudinal trim angle and trim lift coefficient a deflection of 20deg caused only a small additional increase in trim angle and trim lift coefficient.
    Keywords: Aircraft Stability and Control
    Type: NACA RM-SL52D23
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    NASA TECHNICAL REPORTS
  • 28
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    Development of Spoiler Controls for Remote Control of Flying Missiles (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The present report deals with the aerodynamic, constructive, and instrumental development of a spoiler control for remote control of flying missiles.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1210 , ZWB Forschungsbericht; Rept-1717
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    NASA TECHNICAL REPORTS
  • 29
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    Jet Diffusion in Proximity of a Wall (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: When auxiliary jet engines are installed on airframes; as well as in some new designs, the jet engines are mounted in such a way that the jet stream exhausts in close proximity to the fuselage. This report deals with the behavior of the jet in close proximity to a two-dimensional surface. The experiments were made to find out whether the axially symmetric stream tends to approach the flat surface. This report is the last of a series of four partial test reports of the Goettingen program for the installation of jet engines, dated October 12, 1943. This report is the complement of the report on intake in close proximity to a wall.
    Keywords: Aerodynamics
    Type: NACA-TM-1214 , Untersuchungen und Mitteilungen; 3057
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  • 30
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    The Compressible Flow Past Various Plane Profiles Near Sonic Velocity (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In an earlier report UM No.1117 by Gothert,the single-source method was applied to the compressible flow around circles, ellipses, lunes, and around an elongated body of revolution at different Mach numbers and the results compared as far as possible with the calculations by Lamla ad Busemann. Essentially, it was found that with favorable source arrangement the single-source method is in good agreement with the calculations of the same degree of approximation by.Lamla and Busemann. Near sonic velocity the number of steps must be increased considerably in order to sufficiently approximate the adiabatic curve. After exceeding a certain Mach number where local supersonic fields occur already, it was no longer possible, in spite of the substantially increased number of steps, to obtain a systematic solution because the calculation diverged. This result,was interpreted to mean that above this point of divergence the symmetrical type of flow ceases to exist and changes into the unsymmetrical type characterized by compressibility shocks.
    Keywords: Aerodynamics
    Type: NACA-TM-1203 , Untersuchungen und Mitteilurgen; 1471
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  • 31
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    Effect of the Acceleration of Elongated Bodies of Revolution Upon the Resistance in a Compressible Flow (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The problem of the motion of an elongated body of revolution in an incompressible fluid may, as is known, be solved approximately with the aid of the distribution of sources along the axis of the body. In determining the velocity field, the question of whether the body moves uniformly or with an acceleration is no factor in the problem. The presence of acceleration must be taken into account in determining the pressures acting on the body. The resistance of the body arising from the accelerated motion may be computed either directly on the basis of these pressures or with the aid of the so-called associated masses (inertia coefficients). A different condition holds in the case of the motion of bodies in a compressible gas. In this case the finite velocity of sound must be taken into account.
    Keywords: Aerodynamics
    Type: NACA-TM-1230 , Prikladnaya Matematika I Mekhanika; 10; 4; 521-524
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  • 32
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    An Approximate Method for Calculation of the Laminar Boundary Layer with Suction for Bodies of Arbitrary Shape (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Various ways were tried recently to decrease the friction drag of a body in a flow; they all employ influencing the boundary layer. One of them consists in keeping the boundary layer Laminar by suction; promising tests have been carried out. Since for large Reynolds numbers the friction drag of the laminar boundary layer is much lower than that of the turbulent boundary layer, a considerable saving in drag results from keeping the boundary layer laminar, even with the blower power required for suction taken into account. The boundary layer is kept laminar by suction in two ways: first, by reduction of the thickness of the boundary layer and second, by the fact that the suction changes the form of the velocity distribution so that it becomes more stable, in a manner similar to the change by a pressure drop. There by the critical Reynolds number of the boundary layer (USigma*/V) (sub crit) becomes considerably higher than for the case without suction. This latter circumstance takes full effect only if continuous suction is applied which one might visualize realized through a porous wall. Thus the suction quantities required for keeping the boundary layer laminar become so small that the suction must be regarded as a very promising auxiliary means for drag reduction.
    Keywords: Aerodynamics
    Type: NACA-TM-1216
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  • 33
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    High-Speed Wind-Tunnel Investigation of the Lateral Stability Characteristics of a 0.10-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 301 (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was made in the Langley high-speed 7- by 10-foot tunnel to determine the high-speed lateral and directional stability characteristics of a 0.10-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicate that static lateral and directional stability is present throughout the Mach number range investigated although in the Mach number range from 0.75 to 0.85 there is an appreciable decrease in rolling moment due to sideslip. Calculations of the dynamic stability indicate that according to current flying-quality requirements the damping of the lateral oscillation, although probably satisfactory for the sea-level condition, may not be satisfactory for the majority of the altitude conditions investigated
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-Sl9G21A
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  • 34
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    Investigations on the Stability, Oscillation, and Stress Conditions of Airplanes with Tab Control: First Partial Report. Derivation of the Equations of Motion and their General Solutions (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: For the design and the construction of airplanes the control is of special significance, not only with regard to the flight mechhnical properties but also for the proportional arrangement of wing unit, fuselage, and tail unit. whereas these problems may be regarded as solved for direct control of airplane motions, that is, for immediate operation of the control surfaces, they are not clarified as to oscimtions, stability, and stress phenomena occurring in flight motions with Indirect control, ss realized for instance in tab control. Its modus operandi is based on the activation of a tab hinged to the trailing edge & the main control surface. Due to lift and drag variations, mcments originate about the axis of rotation of the main contnol surface which cause an up-or--down floating of the main control surface and thus a change in the direction of the airplane. Since this tab control means flying with free control surface , the treatment of this problem should provide the basis on which to judge stability, oscilhtton, and stress data.The present report is to represent a contribution toward the clarification of the problems arising and, to treat the longitudinal motion of an airplane.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1197 , ZWB Forschungsbericht Nr. 2000; Rept-2000
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  • 35
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    Systematic Investigations of the Effects of Plan Form and Gap between the Fixed Surface and Control Surface on Simple Flapped Wings (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Four component measurements of 12 wings of symmetric profile having flaps with chord ratios t(sub R)/t(sub L) = 0.3 and t(sub R)/t(sub L) = 0.2 are treated in this report. As a result of the investigations, the effects of plan form and gap between fixed surface and control surface have been clarified. Lift, drag, pitching moment, and hinge moment were measured in the control-surface deflection range: -23 deg 〈 or = beta 〈 or = 23 deg and the range of angle of attack: -20 deg 〈 or = alpha 〈 or = 20 deg. Six wings with flaps of small chord (t(sub R)/t(sub L) 〈 0.1) were investigated at large flap settings.
    Keywords: Aerodynamics
    Type: NACA-TM-1206 , ZWB Forschungsbericht; Rept-552/4
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  • 36
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    Flow Pattern in a Converging-Diverging Nozzle (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The present report describes a new method for the prediction of the flow pattern of a gas in the two-dimensional and axially symmetrical case. It is assumed that the expansion of the gas is adiabatic and the flow stationary. The several assumptions necessary of the nozzle shape effect, in general, no essential limitation on the conventional nozzles. The method is applicable throughout the entire speed range; the velocity of sound itself plays no singular part. The principal weight is placed on the treatment of the flow near the throat of a converging-diverging nozzle. For slender nozzles formulas are derived for the calculation of the velocity components as function of the location.
    Keywords: Aerodynamics
    Type: NACA-TM-1215 , Luftfahrtforschung; 91-102
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  • 37
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    Spin Investigation of a 1/29-Scale Model of the Republic XF-91 Airplane with a Conventional Tail Installed (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/29-scale model of the Republic XF-91 airplane with a.conventional-tail arrangement installed. Previously, tests were made on the model with a vee tail installed. The erect spin and recovery characteristics of the model were determined for the normal loading with the wing installed at various amounts of incidence. The spin investigation also included inverted-spin tests, spin-recovery-parachute tests, tests with the center of gravity moved rearward, and tests with external fuel tanks added to the model. In addition, several tail.modifications were tested,on the model in an attempt, to improve the model's spin-recovery characteristics. The results indicate that any fully developed spin obtained on the airplane with the conventional tail installed will be satisfactorily terminated if rudder reversal is accompanied by moving the ailerons with the spin (stick right in a right spin).Decreasing the wing incidence from 6deg to -2deg should have a beneficial effect on the recovery characteristics of the airplane. Recovery characteristics by normal use of controls (full rudder reversal followed by moving the elevators down) will be satisfactory if the wing incidence,of the airplane is -2deg. Installation of external fuel tanks (with or without fuel) will have a somewhat adverse effect on the recovery characteristics of the airplane, but if the recovery technique includes movement of the ailerons to full with the spin, the spin rotation will be terminated rapidly. Varying the position of the center of gravity within the limits indicated to be possible on the airplane should not affect the recovery characteristics.
    Keywords: Aerodynamics
    Type: NACA-RM-SL9E20
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  • 38
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    Two-Dimensional Wing Theory in the Supersonic Range (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The plane problem of the vibrating airfoil in supersonic flow is dealt with and solved within the scope of a linearized theory by the method of the acceleration potential.
    Keywords: Aerodynamics
    Type: NACA-TM-1238 , ZWB Forschungsbericht Nr. 1903; Rept-1903
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  • 39
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    On the Motions of an Oscillating System Under the Influence of Flip-Flop Controls (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: So-called flip-flop controls (also called "on-off-course controls") are frequently preferred to continuous controls because of their simple construction. Thus they are used also for the steering control of airplanes. Such a body possesses-even if one thinks, for instance, only of the symmetric longitudinal motion - three degrees of freedom so that a study of its motions under the influence of an intermittent control is at least lengthy. Thus, it is suggested that an investigation of the basic effect of such a control first be made on a system with one degree of freedom. Furthermore, we limit ourselves in the resent report to the investigation of an "ideal" control where the control surface immediately obeys the command given by the "steering control function". Thus the oscillation properties of the control surface and the defects in linkage, sensing element, and mixing device are, at first, neglected. As long as the deviations from the "ideal" control may be neglected in practice, also the motion of the control surface takes place at the heat of the motion of the principal system. The aim of our investigation is to obtain a survey of the influence of the system and control coefficients on the damping behavior which is to be attained.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1237 , ZWB Untersuchungen und Mitteilungen Nr. 1326; Rept-1326
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  • 40
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    Supplementary Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-2 Airplane (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A supplementary investigation on the stabilization of the Jettisonable nose section of the X-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. It was found that the nose section could be stabilized by the addition of curved fins which could be folded against the fuselage for normal flight.
    Keywords: Aerodynamics
    Type: NACA-RM-L9F22
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  • 41
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    Investigation in Simulated Vertical Descent of the Characteristics of a Cargo-Dropping Device having Extensible Rotating Blades (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The characteristics of a cargo-dropping device having extensible rotating blades as load-carrying surfaces have been studied in simulated vertical descent in the Langley 20-foot free-spinning tunnel. The investigation included tests to determine the variation in vertical sinking speed with load. A study of the blade characteristics and of the test results indicated a method of dynamically balancing the blades to permit proper functioning of the device.
    Keywords: Aerodynamics
    Type: NACA-RM-L9G14
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  • 42
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    Investigation of Stability and Control Characteristics of a 1/10-scale Model of a Canadian Tailless Glider in the Langley Free-flight Tunnel (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation of the stability and control characteristics of a 1/10-scale model of a Canadian tailless glider has been conducted in the 10 Langley free-flight tunnel. The glider designated the N.R.L. tailless glider has a straight center section and outboard panels sweptback 43 deg. along the leading edge of the wing. The aspect ratio is 5.83 and the taper ratio is 0.323. From the results of the investigation and on the basis of comparison with higher-scale static tests of the National Research Council of Canada, it is expected that the longitudinal stability of the airplane will be satisfactory with flap up but unsatisfactory near the stall with flap down. The airplane is expected to have unsatisfactory lateral stability and control characteristics in the design configuration with either flap up or flap down. The model flights showed very low damping of the lateral oscillation. Increasing the vertical-tail area improved the lateral stability, and it appeared that a value of the directional-stability parameter C(sub n beta) of at least 0.002 per degree would probably be necessary for satisfactory lateral flying characteristics. A comparison of the calculated dynamic lateral stability characteristics of the N.R.L. tailless glider with those of a conventional-type sweptback airplane having a similar wing plan form and about the same inclination of the principal longitudinal axis of inertia showed that the tailless glider had poorer lateral stability because of the relatively larger radius of gyration in roll and the smaller damping-in-yaw factor C(sub nr).
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9C28
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  • 43
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    Rough-water Landings of a 0.1-Size Powered Dynamic Model of the XP5Y-1 Flying Boat with Two Types of Afterbody - Langley Tank Model 228 (TED No. NACA DE309) (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A 0.1-size powered dynamic model of a large, high-speed flying boat was landed in Langley tank no. 1 into oncoming waves 4 feet high (full size). The model was tested with two afterbodies of differing lengths (4.12 and 6.63 beams). The short afterbody had a constant angle of dead rise of 22.5deg and a keel angle of 6.5deg. The long afterbody had warped dead rise and a keel angle of 8.5deg. The vertical accelerations were slightly greater and the maximum angular accelerations and maxim= trims were slightly less for the model with the long afterbody than for the model with -the short afterbody. A wave length of 210 feet (full size) imposed the highest accelerations on the model with either the long or the short afterbody.
    Keywords: Aerodynamics
    Type: NACA-RM-SL9B09
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  • 44
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    Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine. II - Performance of Inlet Guide Vanes as Separate Component (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The inlet wide vanes for the supersonic compressor of the XJ55-FF-1 engine were studied as a separate component in order to determine the performance prior to installation in the compressor test rig. Turning angles approached design values, and increased approximately to through the inlet Mach number range from 0.30 to choke. A sharp break in turning angle was experienced when the choke condition was reached. The total-pressure loss through the guide vanes was approximately 1 percent for the unchoked conditions and from 5 to 6 percent when choked.
    Keywords: Aerodynamics
    Type: NACA-RM-SE9E03
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  • 45
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    NACA Conference on Aerodynamic Problems of Transonic Airplane Design (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: During the past several years it has been necessary for aeronautical research workers to exert a good portion of their effort in developing the means for conducting research in the high-speed range. The transonic range particularly has presented a very acute problem because of the choking phenomena in wind tunnels at speeds close to the speed of sound. At the same time, the multiplicity of design problems for aircraft introduced by the peculiar flow problems of the transonic speed range has given rise to an enormous demand for detail design data. Substantial progress has been made, however, in developing the required research techniques and in supplying the demand for aerodynamic data required for design purposes. In meeting this demand, it has been necessary to resort to new techniques possessing such novel features that the results obtained have had to be viewed with caution. Furthermore, the kinds of measurements possible with these various techniques are so varied that the correlation of results obtained by different techniques generally becomes an indirect process that can only be accomplished in conjunction with the application of estimates of the extent to which the results of measurements by any given technique are modified by differences that are inherent in the techniques. Thus, in the establishment of the validity and applicability of data obtained by any given technique, direct comparisons between data from different sources are a supplement to but not a substitute for the detailed knowledge required of the characteristics of each technique and fundamental aerodynamic flow phenomena.
    Keywords: Aerodynamics
    Type: NASA-TM-X-56649 , NACA Conference on Aerodynamic Problems of Transonic Airplane Design; Sep 27, 1949 - Sep 29, 1949; Hampton, VA; United States
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  • 46
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    Preliminary Results of a Free-Flight Investigation of the Static Stability and Aileron Control Characteristics of 1/6 Scale Models of the Bell MX-776 (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation of the static longitudinal stability, static directional stability, and aileron control characteristics at transonic and supersonic speeds is being made of 1/6 scale rocket-propelled model of the Bell MX-776. A stability investigation has been made of two symmetrical models with controls undeflected and centers of gravity one-half and one-body diameter, respectively, ahead of the equivalent design center-of-gravity location of the full-scale version. Both models developed large normal-force coefficients in both the subsonic and supersonic ranges which indicated longitudinal instability at low angles of attack. The side-force coefficients were small for both models and indicated that the models were directionally stable. A possible tendency toward dynamic directional instability in the transonic region was indicated by short-period oscillations of the side forces. The results showed a partial-span inboard aileron to be ineffective or to cause negative control in the the transonic region when deflected approximately 5 deg but not when deflected 10 deg. An investigation of drag showed it to increase with a rearward movement of the center of gravity. This indicates an increase in the trim angle of attack as could be caused by a decrease in static stability.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9D21
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  • 47
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    Exact Calculation of Laminar Boundary Layer in Longitudinal Flow over a Flat Plate with Homogeneous Suction (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Lately it has been proposed to reduce the friction drag of a body in a flow for the technically important large Reynolds numbers by the following expedient: the boundary layer, normally turbulent, is artificially kept laminar up to high Reynolds numbers by suction. The reduction in friction drag thus obtained is of the order of magnitude of 60 to 80 percent of the turbulent friction drag, since the latter, for large Reynolds numbers, is several times the laminar friction drag. In considering the idea mentioned one has first to consider whether suction is a possible means of keeping the boundary layer laminar. This question can be answered by a theoretical investigation of the stability of the laminar boundary layer with suction. A knowledge, as accurate as possible, of the velocity distribution in the laminar boundary layer with suction forms the starting point for the stability investigation. E. Schlichting recently gave a survey of the present state of calculation of the laminar boundary layer with suction.
    Keywords: Aerodynamics
    Type: NACA-TM-1205 , Schriften der Deutschen Akademie der Luftfahrtforschung; 8; 1
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  • 48
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    Larger shocks of 1947 (1948)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Pasadena, California Institute of Technology Pasadena, vol. 1947, no. 6, pp. 126, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1948
    Keywords: Seismology ; Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 49
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    Über die tektonisch-mechanischen Folgerungen aus den großen anatolischen Erdbeben des letzten Dezenniums (1948)
    In:  Geol. Rundschau, New York, Allerton Press, vol. 36, no. 2, pp. 77-83, pp. L01606, (ISSN: 1340-4202)
    Details
    Publication Date: 1948
    Keywords: Seismicity ; Fault zone ; NAF ; SAF ; Turkey ; Structural geology ; 1939 ; Earthquake
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  • 50
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    Deep-focus earthquakes in the Mediterranean region (1948)
    In:  Geofisica Pura e Applicata, Pasadena, California Institute of Technology Pasadena, vol. 12, no. 6, pp. 130-134, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1948
    Keywords: Seismology ; Seismicity ; Source parameters ; Hypocentral depth
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  • 51
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    Erdbebengeographie und Dynamik der Erdkruste (1948)
    In:  Die Naturwissenschaften, Pasadena, California Institute of Technology Pasadena, vol. 35, no. 6, pp. 196-202, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1948
    Keywords: CRUST ; Tectonics ; Seismology ; Seismicity
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  • 52
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    Earthquake study in Southern California 1947 (1948)
    In:  Trans., Am. Geophys. Union, Pasadena, California Institute of Technology Pasadena, vol. 29, no. 6, pp. 406-407, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1948
    Keywords: Seismology ; Seismicity ; EOS
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  • 53
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    Die San José-Schildlaus (1948)
    In:  Natur und Volk 78; p.58-65
    Details
    Publication Date: 1948
    Description: Qualitative Schilderung des Befalls durch die und der Verbreitung der San José-Schildlaus anhand einiger Beobachtungen an Obstgewächsen in Baden-Württemberg und teilw. Nord-Bayern. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Baden-Württemberg ; 1946-1947 ; Pflanzenschädling ; Obst
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    BIBLIOGRAPHY INKA BB
  • 54
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    Wind und Pflanzenschädlinge (1948)
    In:  Wetter und Klima 1; p.316
    Details
    Publication Date: 1948
    Description: In einem kleinen allgemeinen Kommentar wird der Zusammenhang zwischen Wind (v.a. Windrichtung) und anderen Wetterbedingungen in Verbindung mit der Ausbreitung des Kartoffelkäfers und des Borkenkäfers genannt. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1943-46 ; Kartoffeln ; Forst ; Pflanzenschädling ; Hackfrüchte
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    BIBLIOGRAPHY INKA BB
  • 55
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    Kahlfraß an Senf durch die Rübenblattwespe (Athalia colibri) (1948)
    In:  Nachr.-Bl. Deutscher Pflanzenschutzdienst 2; p.3-5
    Details
    Publication Date: 1948
    Description: Der Autor bringt das starke Auftreten des Kohlweißlings und der Rübenblattwespe, die verheerende Schäden an Kohl- bzw. Senffeldern verursachten, mit der Trockenheit des Sommers 1947 in weiten Teilen Nord-, Mittel- und Ostdeutschlands in Verbindung. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Thüringen, Sachsen, Sachsen-Anhalt, Brandenburg ; 1947 ; Pflanzenschädling ; Kohl ; Sonderkulturen ; Gemüse
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  • 56
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    Über das Auftreten und die Bekämpfung des Rüben-Derbrüsslers Bothynoderes (Cleonus) punctiventris im Jahre 1948 sowie über einige andere schädliche Rüssler des Rübenbaues (1948)
    In:  Nachr. Bl. Deutscher Pflanzenschutzdienst, Heft 3/4, Jahrgang 2, p. 33-36
    Details
    Publication Date: 1948
    Description: Allgemeine Beobachtungen zur Lebensweise des Rüben-Derbrüsslers KATASTER-BESCHREIBUNG: Zusammenhang zwischen dem Massenauftreten des Käfers und der Witterung im Frühjahr und Sommer KATASTER-DETAIL: Delta T: T 〈 12-14°C, dann Ende der Winterruhe; Delta T+, dann Flugbeginn; Delta Nied (Frühjahr und Sommer) +, dann Massenauftreten +;
    Keywords: Sachsen-Anhalt ; 1948 ; Zuckerrüben ; Niederschlag ; Pflanzenschädling ; Temperatur ; Trockenheit ; Witterung
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  • 57
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    Zur Phänologie des Rüben-Derbrüsslers, Bothynoderes (Cleonus) punctiventris (1948)
    In:  Nachr. Bl. Deutscher Pflanzenschutzdienst, p. 133
    Details
    Publication Date: 1948
    Description: Verbale Beschreibung zur Verbeitung und zum Jahreszyklus des Rüben-Derbrüsslers KATASTER-BESCHREIBUNG: Zusammenhang zwischen Temperatur und Jahreszyklus des Käfers KATASTER-DETAIL: Delta T: T (Luft)〉 12-14°C, dann Ende der Winterruhe
    Keywords: Deutschland ; 1946-48 ; Zuckerrüben ; Pflanzenschädling ; Temperatur
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  • 58
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    Die Wandergewohnheiten und der Flug des großen Kohlweißlings (Pieris brassicae L.) (1948)
    In:  Z. Pflanzenkrankheiten (Pflanzenpathol.) Pflanzenschutz, Nov./Dez., p. 335-341,
    Details
    Publication Date: 1948
    Description: Bericht über allgemeine Beobachtungen zum Flug und zu den Wandergewohnheiten des Großen Kohlweißlings KATASTER-BESCHREIBUNG: Einfluss von Wind und Sonnenscheindauer auf den Flug des Kohlweißlings KATASTER-DETAIL: Wind 〉 20km/h, dann kein Flug; Delta Sonn +, dann Flug +;
    Keywords: Deutschland ; 1942-48 ; Pflanzenschädling ; Temperatur ; Sonnenscheindauer ; Kohl
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  • 59
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    Bericht über die im Winter 1947/48 durchgeführten Untersuchungen von Raps- und Rübsenproben auf Befall mit Rapserdfloh-(Psylloides chrysocephala L.)-Larven (1948)
    In:  Nachr. Bl. Deutscher Pflanzenschutzdienst, p. 38-39
    Details
    Publication Date: 1948
    Description: Bericht über die Laboruntersuchungen von Raps- und Rübsenproben auf den Befall mit Rapserdflohlarven KATASTER-BESCHREIBUNG: Einfluss von Temperatur und Trockenheit auf die Entwicklung des Rapserdflohs KATASTER-DETAIL: Delta T + und Delta Nied -, dann spätere Eiablage; Delta Nied -, dann Entwicklung der Eier -
    Keywords: Mecklenburg, Thüringen, Sachsen, Brandenburg ; 1947-1948 ; Luftfeuchte ; Pflanzenschädling ; Temperatur ; Raps
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  • 60
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    Die Überwinterung der grünen Pfirsichblattlaus Myzodes persicae (Sulz) und die Auswirkungen der Überwinterungsquellen auf den Massenwechsel im Sommer (1948)
    In:  Nachrichtenblatt für den Deutschen Pflanzenschutzdienst, Heft 7/8, p.105-112
    Details
    Publication Date: 1948
    Description: Untersuchungen im Berliner Botanischen Garten, im Institut für Züchtungsforschungen in Müncheberg/Mark und im Obstbezirk des Alten Landes bei Hamburg/Stade über das Auftreten von Larven, die aus überwinterten Eiern auf Obstbäumen geschlüpft sind sowie Untersuchungen zur Temperaturempfindlichkeit der Fundatrix-Larven und der Sommerform von Myzodes Persicae im Labor. KATASTER-BESCHREIBUNG: Zusammenhang ziwschen Temperatur, Niederschlag sowie relativer Luftfeuchte und dem Überwinterungserfolg KATASTER-DETAIL: Delta T -, Delta Nied ++, Delta Relf +, dann Myzodes persicae -; T 〈 -9°C, dann Myzodes persicae -; T 〈 -12°C (d 〉 1), dann Tod
    Keywords: Deutschland, Labor ; 1933 - 1948 ; Niederschlag ; Pflanzenschädling ; Temperatur
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  • 61
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    An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability.
    Keywords: Aerodynamics
    Type: NACA-RM-A7J13
    Format: application/pdf
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  • 62
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    The Development of Cambered Airfoil Sections Having Favorable Lift Characteristics at Supercritical Mach Numbers (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to have lift characteristics at supercritical Mach numbers which are favorable in the sense that the abrupt loss of lift, characteristic of the usual airfoil section at Mach numbers above the critical, is avoided. Aerodynamic characteristics determined, from two-dimensional windtunnel tests at Mach numbers up to approximately 0.9 are presented for each of the derived airfoils. Comparisons are made between the characteristics of these airfoils and the corresponding characteristics of representative NPiCA 6-series airfoils. The experimental results confirm the design expectations in demonstrating for the NACA S-series airfoils either no variation, or an Increase from the low-speed design value, In the lift coefficient at a constant angle of attack with increasing Mach number above the critical. It was not found possible to improve the variation with Mach number of the slope of the lift curve for these airfoils above that for the NACA 6-series airfoils. The drag characteristics of the new airfoils are somewhat inferior to those of the NACA 6- series with respect to divergence with Mach number, but the pitching-moment characteristics are more favorable for the thinner new sections In demonstrating somewhat smaller variations of moment coefficient with both angle of attack and Mach number. The effect on the aero&ynamic characteristics at high Mach numbers of removing the cusp from the trailing-edge regions of two 10-percent-chord-thick NACA 6-series airfoils is determined to be negligible.
    Keywords: Aircraft Stability and Control
    Type: NACA-TN-1771
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  • 63
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    Investigation of the Penetration on an Air Jet Directed Perpendicularly to an Air Stream (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the penetration of a circular air Jet directed perpendicularly to an air stream as a function of Jet density, Jet velocity, air-stream density, air-stream velocity, Jet diameter, and distance downstream from the Jet. The penetration was determined for nearly constant values of air-stream density at two tunnel velocities, four Jet diameters, four positions downstream of the Jet, and for a large range of Jet velocities and densities. An equation for the penetration was obtained in terms of the Jet diameter, the distance downstream from the jet, and the ratios of Jet and air-stream velocities and densities.
    Keywords: Aerodynamics
    Type: NACA-TN-1615
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  • 64
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    Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane with Wing-Tip Tanks Installed (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the spin and recovery characteristics of a 1/24-scale model of the Grumman XF9F-2 airplane with wing-tip tanks installed has been conducted-in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect spin and recovery characteristics of the model for a range of possible loadings of the tip tanks were determined. Spin and recovery characteristics without tanks were determined in a previous investigation. The model results indicated that the airplane spins will generally be oscillatory and that recoveries will be satisfactory for all loadings by normal recovery technique (full rudder reversal followed approximately one-half turn later by moving the elevator down). The rudder force necessary for recovery should be within the physical capability of the pilot but the elevator force may be excessive so that some type of balance or booster might be necessary, or it might be necessary to jettison the wing-tip tanks.
    Keywords: Aerodynamics
    Type: NACA-RM-SL9F01
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  • 65
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    Supplementary Investigation to Determine the Effects of Center-of-Gravity Position on the Spin, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultee 7002 Airplane (Flying Mock-up of XF-92) (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A supplementary wind-tunnel investigation has been conducted to determine the effect of rearward positions of the center of gravity on the spin, longitudinal-trim, and tumbling characteristics of the 1/20-scale model of the Consolidated Vultee 7002 airplane equipped with the single vertical tail. A few tests were also made with dual vertical tails added to the model. The model was ballasted to represent, the airplane in its approximate design gross weight for two center-of-gravity positions, 3O and 35 percent of the mean aerodynamic chord. The original tests previously reported were for a center-of-gravity position of 24 percent of the mean aerodynamic chord.
    Keywords: Aerodynamics
    Type: NACA-RM-SL9B24
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  • 66
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    A Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the MX-838 (XB-51) Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: At the request of the Air Material Command, U. S. Air Force, a theoretical study has been made of the dynamic lateral stability characteristics of the MX-838 (XB-51) airplane. The calculations included the determination of the neutral-oscillatory-stability boundary (R = 0), the period and time to damp to one-half amplitude of the lateral oscillation, end the time to damp to one-half amplitude for the spiral mode. Factors varied in the investigation were lift coefficient, wing incidence, wing loading, and altitude. The results of the investigation showed that the lateral oscillation of the airplane is unstable below a lift coefficient of 1.2 with flaps . deflected 40deg but is stable over the entire speed range with flaps deflected 20deg or 0deg. The results showed that satisfactory oscillatory stability can probably be obtained for all lift coefficients with the proper variation of flap deflection and wing incidence with airspeed. Reducing the positive wing incidence improved the oscillatory stability characteristics. The airplane is spirally unstable for most conditions but the instability is mild and the Air Force requirements are easily met.
    Keywords: Aerodynamics
    Type: NACA-RM-SL8K10
    Format: application/pdf
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  • 67
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    Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-type 4000.pound-thrust turboJet engine for a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.02 to 1.86 are presented and the experimental and analytical methods employed are discussed. By means of suitable generalizing factors applied to the measured performance data, curves were obtained from which the engine performance at any altitude for a given ram pressure ratio can be estimated. The data presented include the windmilling drag characteristics of the turbojet engine for the ranges of altitudes and ram pressure ratios covered by the performance data.
    Keywords: Aerodynamics
    Type: NACA-RM-E8F09-Pt-1
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  • 68
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    Supplementary Investigation in the Langley 20-Foot Free-Spinning Tunnel of the Spin and Recovery Characteristics of a 0.057-Scale Model of the Chance Vought XFU-1 Airplane, Ted No. NACA DE 311 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the effects of decreasing the rudder deflection, of decreasing the rudder span, and of differential rudder movements on the spin and recovery characteristics of a 0.057-scale model of the Chance Vought XF7U-1 airplane. The results indicated that decreasing the rudder span or the rudder deflections, individually or jointly, did not seriously alter the spin or recovery characteristics of the model; and recovery by normal use of controls (full rapid rudder reversal followed l/2 to 1 turn later by movement of the stick forward of neutral) remained satisfactory. Linking the original rudders so that the inboard rudder moves from full with the spin to neutral while the outboard rudder moves from neutral to full against the spin will also result in satisfactory spin and recovery characteristics. Calculations of rudder-pedal forces for recovery showed that the expected forces would probably be within the capabilities of a pilot but that it would be advisable to install some type of boost in the control system to insure easy and rapid movement of the rudders.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9H30a
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  • 69
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    Flight Measurements of the Longitudinal Stability and Control Characteristics of the Grumman F8F-1 Airplane, TED No. NACA 2379 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. These tests were made between February and June of 1947- The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compressibility effects at higher Mach numbers. The lateral and directional stability and control characteristics of the subject airplane have already been reported (reference 1). Also presented in this paper is a discussion of the normal accelerations induced by yawing velocity and sideslip which were considered ob,jectionable by the pilot for this airplane. A discussion of the undesirable accelerations has been included with a view towards formulating some flying-qualities requirements limiting them.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8H27
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  • 70
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    High-Speed Wind-Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 0.10-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE301 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was made in the Langley high-speed 7-by 10-foot tunnel to determine the high-speed longitudinal stability end con&o1 characteristics of a 0.01-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicated that the lift and drag force breaks occurred at a Mach number of about 0.76. The aerodynamic-center position moved rearward after the force break and control position stability was present for all Mach numbers up to a Mach number of 0.80.
    Keywords: Aerodynamics
    Type: NACA-RM-SL8K16
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  • 71
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    Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the North American XP-86 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the North American XP-86 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the design gross weight loading. The long-range loading was also investigated and the effects of extending slats and dive flaps were determined. In addition, the investigation included the determination of the size of spin-recovery parachute required for emergency recovery from demonstration spins, the rudder force required to move the rudder for recovery, and the best method for the pilot to escape if it should become necessary to do so during a spin. The results of the investigation indicated that the XP-86 airplane will probably recover satisfactorily from erect and inverted spins for all possible loadings. It was found that fully extending both slats would be beneficial but that extending the dive brakes would cause unsatisfactory recoveries. It was determined that a 10.0-foot-diameter tail parachute with a drag coefficient of 0.7 and with a towline 30.0 feet long attached below the jet exit or a 6.0-foot-diameter wingtip parachute opened on the outer wing tip with a towline 6.0 feet long would insure recoveries from any spins obtainable. The rudder-pedal force necessary to move the rudder for satisfactory recovery was found to be within the physical capabilities of the pilot.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8D22
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  • 72
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    Preliminary Results of an Investigation by the Wing-Flow Method of the Longitudinal Stability Characteristics of a 1/50-Scale Semispan Model of the McDonnell XP-88 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This paper presents the results of measurements of longitudinal stability of a 1/50-scale model of the XP-88 airplane by the wing-flow method. Lift, rolling-moment, hinge-moment, and pitching-moment characteristics as well as the downwash at the tail were measured over a Mach number range from approximately 0.5 to 1.05 at Reynolds numbers below 1,000,000. No measurements of drag were obtained. No abrupt changes due to Mach number were noted in any of the parameters measured. The data indicated that the wing was subject to early tip stalling; that the tail effectiveness decreased gradually with increasing Mach number up to M = 0.9, but increased again at higher Mach numbers; that the variation of downwash with angle of attack did not change appreciably with Mach number except between 0.95 and 1.0 where d(epsilon)/d(alpha), decreased from 0.46 to 0.32; that at zero lift with a stabilizer setting of -1.5 deg there was a gradually increasing nosing-up tendency with increasing Mach number; and that the control-fixed stability in maneuvers at constant speed gradually increased with increasing Mach number.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8E28A
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  • 73
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    Free-Spinning-Tunnel Tests of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the spin and recovery characteristics of a 0.057-scale model of the Chance Vought XF7U-1 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics were determined, as were also the effects of extending the wing slats, of center-of-gravity movement, and-of variation in the mass distribution. The investigation also included wing-tip spin-recovery-parachute tests, pilot-escape tests, and rudder-control-force tests. The investigation indicated that the spin and recovery characteristics of the airplane will be satisfactory for all conditions. It was found that a single 4.24-foot (full-scale) parachute when opened alone from the outboard wing tip or two 8.77-foot (full-scale) parachutes when opened simultaneously, one from each wing tip, would effect satisfactory emergency recoveries (the drag coefficients of the parachutes, based on the surface area of the parachute, were 0.83 and 0.70 for the 4.24- and 8.77-foot parachutes, respectively). The towline length in both cases was 25 feet (full scale). Tests results showed that, if the pilot should have to leave the airplane during a spin, he should jump from the outboard side (left side in a right spin) of the cockpit. The rudder-control force necessary for recovery from a spin was found to be rather high but appeared to be within the upper limits of a pilot's capabilities.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8A13
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  • 74
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    Ditching Tests of a 1/20-Scale Model of the Northrop B-35 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tests of a 1/20-scale dynamically similar model of the Northrop B-35 airplane were made to study its ditching characteristics. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds,and conditions of damage were simulated during the investigation. The ditching characteristics were determined by visual observation and from motion-picture records and time-history acceleration records. Both longitudinal and lateral accelerations were measured. Results are given in tabular form and time-history acceleration curves and sequence photographs are presented. Conclusions based on the model investigation are as follows: 1. The best ditching of the B-35 airplane probably can be made by contacting the water in a near normal landing attitude of about 9 deg with the landing flaps full down so as to have a low horizontal speed. 2. The airplane usually will turn or yaw but the motion will not be violent. The maximum lateral acceleration will be about 2g. 3. If the airplane does not turn or yaw immediately after landing, it probably will trim up and then make a smooth run or porpoise slightly. The maximum longitudinal decelerations that will be encountered are about 6g or 7g. 4. Although the decelerations are not indicated to be especially large, the construction of the airplane is such that extensive damage is to be expected, and it probably will be difficult to find ditching stations where crew members can adequately brace themselves and be reasonably sure of avoiding a large inrush of water.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8A29
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  • 75
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    Hydrodynamic Characteristics of an Aerodynamically Refined Planing-Tail Hull (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The hydrodynamic characteristics of an aerodynamically refined planing-tail hull were determined from dynamic model tests in Langley tank no. 2. Stable take-off could be made for a wide range of locations of the center of gravity. The lower porpoising limit peak was high, but no upper limit was encountered. Resistance was high, being about the same as that of float seaplanes. A reasonable range of trims for stable landings was available only in the aft range of center-of-gravity locations.
    Keywords: Aerodynamics
    Type: NACA-RM-L8G16
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  • 76
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    Investigation of the Flying Mock-Up of Consolidated Vultee XP-92 Airplane in the Ames 40- by 80-Foot Wind Tunnel: Pressure Distributions (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report contains the results of the wind tunnel investigation of the pressure distribution on the flying mock-up of the Consolidated Vultee XP-92 airplane. Data are presented for the pressure distribution over the wing, vertical tail and the fuselage, and for the pressure loss and rate of flow through the ducted fuselage. Data are also presented for the calibration of two airspeed indicators, and for the calibration of angle-of-attack and sideslip-angle indicator vanes.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8D08
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  • 77
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    An Investigation of the McDonnell XP-85 Airplane in the Ames 40- by 80-Foot Wind Tunnel: Pressure-Distribution Tests (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Pressure measurements were made during wind-tunnel tests of the McDonnell XP-85 parasite fighter. Static-pressure orifices were located over the fuselage nose, over the canopy, along the wing root, and along the upper and lower stabilizer roots. A total-pressure and static-pressure rake was located in the turbojet engine air-intake duct. It was installed at the station where the compressor face would be located. Pressure data were obtained for two airplane conditions, clean and with skyhook extended, through a range of angle of attack and a range of yaw.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8J22
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  • 78
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    Investigation of the Aerodynamic and Icing Characteristics of a Recessed Fuel Cell Vent Assembly. I: Rear Wall Vent Tube Mounting (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-RM-E8A27b
    Format: application/pdf
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  • 79
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    Wind-Tunnel Measurements on the Henschel Missile "Zitterrochen" in Subsonic and Supersonic Velocities (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: At the request of the Henschel Aircraft Works. A. G. Berlin. three models of the missile "Zitterrochen" were investigated at subsonic velocities.(open jet 215-millimeter diameter) and at supersonic velocities (open jet 110 by 130 millimeters) in order to determine the effect of various wing forms on the air forces and moments. Three-component measurements were taken, and one model was also investigated with deflected control plates.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1159 , DLUM-3122 , Deutsche Luftfahrtforschung, Untersuchungen und Mitteilungen
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  • 80
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    Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was determined in investigations of the complete engine in the NACA Cleveland altitude wind tunnel. Characteristics are presented as functions of the total-pressure ratio across the turbine and of turbine speed and gas flow corrected to sea-level conditions. Three turbine nozzles of different areas were used to determine the area that gave optimum performance. Inasmuch as tail-pipe nozzles of different diameters were investigated in combination with the standard turbine nozzle, the effect of varying discharge conditions on turbine operation could be observed. The investigations covered a range of pressure attitudes from 5000 to 40,000 feet. The engine was investigated over the entire operable range of speeds at each altitude. At pressure altitude of 30,000 feet, the effect on turbine operation of varying the ram pressure ration over a range from 1.10 to 1.77 was evaluated. An altitude effect was apparent when turbine pressure ratio was plotted against corrected turbine speed but it was so slight as to be negligible insofar as the turbine efficiencies were concerned. A maximum turbine efficiency of slightly more than 82 percent was obtained with the configuration using the standard turbine nozzle and the low-flow compressor. This efficiency, which is somewhat lower than the actual turbine efficiency, is uncorrected for accessories drive power, bearing friction, tail-pipe pressure drop, compressor thermal radiation, and introduction of turbine-disk cooling air into the gas stream. Changes in the ram pressure ratio had a negligible effect on the turbine efficiency.
    Keywords: Aerodynamics
    Type: NACA-RM-E8F09d
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  • 81
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    An Investigation of the Aerodynamic Characteristics of a 3/4-Scale Model of the EX-3 Pine-Cone-Head Pellet in the Langley High-Speed 7-by 10-Foot Wind Tunnel (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the Ex-3 pine-cone-head pellet was made in the Langley high-speed 7-by 10-foot wind tunnel to determine the static force and moment characteristics at high Mach numbers with the reference center of gravity located at 37.5 percent of the over-all length aft of the nose. For this center-of-gravity location there were no secondary trim positions, and the center-of-pressure position was not appreciably affected by Mach number.
    Keywords: Aerodynamics
    Type: NACA-RM-SL8G15
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  • 82
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    Tank Tests of a Powered Model of a Compression Plane, NACA Model 171A-2 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The compression plane is intended for operation on or close to the surface of the water, and has a hull with a concave bottom which forms the upper surface of a tunnel into which air is forced under pressure to support part of the load. The results of the tests made in Langley tank no. 1 include values of the horizontal forces, trimming moment, and static pressure in the tunnel for a wide range of loads and speeds and two power conditions, and are presented in the form of curves against speed with load as a parameter. The results are scaled up to 10 times the model size for three conditions at which the model is self-propelled at a steady speed. Lift is obtained from the static pressure of air in the tunnel. In general, the ratio of the gross load to the total resistance increases with increase in load and decrease in speed. This ratio varies between l-7 and 5.7 at high speeds and has a maximum value of 7. The total resistance is nearly the same for both power conditions except at low speeds and heavy loads. No abrupt change in forces on the hull or flow around the hull occurs in. the region of zero draft. The centers of pressure are generally far aft. At the most efficient trim (1.2'), considerable bow-up moment would be required for practicable operation. There is no abrupt transition from the air-borne to the water- borne condition.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8G02
    Format: application/pdf
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  • 83
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    Calculations of the Dynamic Stress of Several Airplane Wings in Various Gusts (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A series of calculations of the dynamic response of airplane wings to gusts were made with the purpose of showing the relative response of a reference airplane, the DC-3 airplane, and of newer types of airplanes represented by the DC-4, DC-6, and L-49 airplanes. Additional calculations were made for the DC-6 airplane to show the effects of speed and altitude. On the basis of the method of calculation used and the conditions selected for analysis, it is indicated that: 1) The newer airplanes show appreciably greater dynamic stress in gusts then does the reference airplane; 2) Increasing the forward speed or the operating altitude results in an increase of the dynamic stress ratio for the gust with a gradient distance of 10 chords.
    Keywords: Aerodynamics
    Type: NACA-RM-SL8F22
    Format: application/pdf
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  • 84
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    Measurements of the Longitudinal Stability and Control and Stalling Characteristics of a North American P-51H Airplane (AAF No. 4-64164) (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Flight tests have been made to determine the longitudinal stability and control and stalling characteristics of a North American P-51H airplane. The results indicate that the airplane has satisfactory longitudinal stability in all the flight conditions tested at normal loadings up to 25,000 feet altitude. At Mach numbers above 0.7, the elevator push force required for longitudinal trim decreased somewhat because of compressibility effects. The elevator stick force per g in accelerated turns at the forward center-of-gravity position of 24 percent mean aerodynamic chord above 250 miles per hour was in excess of the required limits at both 5,000 and 25,OOO feet altitude. The longitudinal-trim-force changes due to flaps and power were small, but the rudder-trim-force change with power change was high. The stalling characteristics in all the conditions tested were satisfactory.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8B24
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  • 85
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    Ditching Tests of a 1/24-Scale Model of the Lockheed XR60-1 Airplane, TED No. NACA 235 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The ditching characteristics of the Lockheed XR60-1 airplane were determined by tests of a 1/24-scale dynamic model in calm water at the Langley tank no. 2 monorail. Various landing attitudes, flap settings, speeds, and conditions of damager were investigated. The ditching behavior was evaluated from recordings of decelerations, length of runs, and motions of the model. Scale-strength bottoms and simulated crumpled bottoms were used to reproduce probable damage to the fuselage. It was concluded that the airplane should be ditched at a landing attitude of about 5 deg with flaps full down. At this attitude, the maximum longitudinal deceleration should not exceed 2g and the landing run will be bout three fuselage lengths. Damage to the fuselage will not be excessive and will be greatest near the point of initial contact with the water.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8E17
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  • 86
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    Maintaining Laminar Flow in the Boundary Layer using a Swept-Back Wing (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The positions of boundary-layer transition were ascertained experimentally for a swept-back wing and a wing without sweepback which were alike in all other respects and were compared for the same angle of attack (R(sub e) = 5.6 x 10(exp 5)). The swept-back wing in a definite range of angle of attack resulted in a backward shift of the transition point on the suction side of the wing. The favorable effect of sweepback on the position of the transition point is confirmed, consequently. In addition to decreasing the drag at high Mach numbers, the swept-back wing is acknowledged to have additional advantages. These are: (1) Decrease of the pressure drag. The reduction factor is approximately equal to the cosine of the angle of sweepback. (2) Backward shift of the transition point. There are no known experiments which establish experimentally the advantage anticipated. It appeared justifiable, therefore, to carry out some fundamental experiments which might furnish some idea of the magnitude of the advantage expected. Such an experiment is reported in what follows; the advantage of the sweepback appears clearly.
    Keywords: Aerodynamics
    Type: NACA-TM-1180 , Untersuchungen und Mitteilungen; 3151
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  • 87
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    Longitudinal Stability Characteristics of a 1/40-Scale Model of a Proposed Configuration of the XF-91 Airplane Measured by the Wing-Flow Method (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report presents the results of an investigation in the transonic speed range of the longitudinal stability characteristics of a proposed configuration for the Republic XF-91 airplane. The tests covered a Mach number range of 0.55 to 1.05 and a Reynolds number range from 400,000 to 1,375,000. Lift, pitching-moment, and rolling-moment characteristics of the half model and the hinge moments on the all-moving tail were measured. The downwash factor delta x epsilon / delta x alpha at the tail was determined from the pitching-moment data. A calculation of the elevator deflection and stick force required for trim was also made. It was found that the variation of force and moment coefficients was linear through the test angle-of-attack range of -1 deg to 8 deg at any Mach number; that the stability increased markedly at Mach numbers above 0.85; that the effectiveness of the tail in producing pitching moments decreased about one-third with increasing Mach numbers and that the value of the downwash factor, delta x epsilon / delta x alpha, at the tail decreased from about 0.35 at a Mach number of 0.85 to about zero at a Mach number near 0.95 and became slightly negative at higher Mach numbers. The calculated values of stick force per g and elevator deflection per g, assuming no aerodynamic balance, increased rapidly above a Mach number of 0.85.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8K17
    Format: application/pdf
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  • 88
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    Longitudinal Trim and Tumble Characteristics of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane, TED NO. NACA DE311 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Based on results of longitudinal trim and tumble tests of a 0.057-scale model of the Chance Vought XF7U-1 airplane, the following conclusions regarding the trim and tumble characteristics of the airplane have been drawn: 1. The airplane will not trim at any unusual or uncontrolled angles of attack. 2. The airplane will not tumble with the center of gravity located forward of 24 percent of the mean aerodynamic chord. When the center of gravity is located at 24 percent of the mean aerodynamic chord and slats are extended and elevators are deflected full up, the airplane may tumble if given an external positive pitching moment. 3. The tumbling motion obtained will be readily terminated by deflecting the elevators full down so as to oppose the rotation. 4. The accelerations encountered during an established tumble may be dangerous to the pilot and, therefore, action should be taken to terminate a tumble immediately upon its inception. 5. Simultaneous opening of two wing-tip parachutes having diameters of 4 feet or larger and having drag coefficients of approximately 0.7 will effectively terminate the tumble. 6. Model results indicate that the pilot will not be struck by the airplane if it becomes necessary to leave the airplane during a tumble. The pilot may require aid from an ejection-seat arrangement.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8F14
    Format: application/pdf
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  • 89
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    Investigation of the Stability and Control Characteristics of a 1/10-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley Free-Flight Tunnel, TED No. NACA DE306 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: At the request of the Bureau of Aeronautics, Navy Department, a stability and control investigation of a 1/10-scale model of the Chance Vought XF7U-1 airplane has been conducted in the Langley free-flight tunnel. Results of force end flight tests to determine the power-off stability and control characteristics of the model with slats retracted and extended are presented herein. The longitudinal and lateral stability characteristics were satisfactory for both the slats retracted and extended conditions over the lift range up to the stall. With the slats retracted, the stall was fairly gentle but the model rolled off out of control. With the slats extended, control could be maintained at the stall so that the wings could be kept level even as the model dropped.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8A19
    Format: application/pdf
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  • 90
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    Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 317 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the spin and recovery characteristics of a scale model of the Grumman XF9F-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the flight loading were determined. The investigation also included spin-recovery-parachute, pilot-escape, and rudder-pedal- . force tests. The recovery characteristics of the model were satisfactory for all configurations tested. Spins for the normal control configuration were oscillatory in roll and yaw. Deflecting the leading-edge flaps or the dive brakes did not change the spin and recovery characteristics of the model noticeably. A 10.0-foot tail parachute or a 6.0-foot wing-tip parachute (drag coefficient of 0.75) was found to be effective for recoveries from demonstration spins. The rudder forces in the spin appeared to be within the capabilities of the pilot.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL7L09
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  • 91
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    Ditching Tests of Two Models of the Army B-36 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The ditching characteristics of the Army B-36 airplane were determined by testing 1/20- and 1/30-scale dynamic models in calm water in Langley tank no. 2 and at the outdoor catapult. The scope of the tests consisted of ditching the models at various conditions of simulated damage, landing attitudes, and speeds, with various flap settings using several degrees of restraint of the flap hinges. The ditching behavior was evaluated from recordings of deceleration, length of run, and motions of the models. The results showed that the airplane should be ditched at an attitude of about 9 deg with flaps full down. The probable ditching behavior will be a smooth run with a maximum longitudinal deceleration of 3g to 4g and a landing run of 4 to 5 fuselage lengths. Structural failure of the underside of the fuselage will not seriously affect the behavior of the airplane.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8B25
    Format: application/pdf
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  • 92
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    Spin Tests of 1/20-Scale Models of the Chance Vought Revised XF6U-1 and F6U-1 Airplanes, TED No. NACA 2390 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel on the 1/20-scale model of the Chance Vought XF6U-1 airplane altered to represent the XF6U-1 airplane as it will be spin-tested in flight, and also altered to represent the F6U-1 airplane as it will be produced for service use. Spin tests were made to determine the effects of control settings and movements at the normal loading. The results show that the spins obtained on the revised XF6U-1 airplane will be oscillatory in roll and yaw and that recoveries by rudder reversal will be rapid. Model test results indicate that the F6U-1 airplane will probably not spin. Inasmuch as the results of this investigation show that the new designs are as good as or better than the original XF6U-1 design in regard to spin recovery, it is felt that the conclusions and recommendations reached for the original design can be applied to the new designs for all loading conditions.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8F03
    Format: application/pdf
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  • 93
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms September 10, 1947 to September 15, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from September 10, 1947 to September 15, 1947, are presented.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L8C31
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  • 94
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    Measurements in Flight of the Longitudinal-Stability Characteristics of a Republic YF-84A Airplane (Army Serial No. 45-59488) at High Subsonic Mach Numbers (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A brief investigation was made of the longitudinal-stability characteristics of a YF-84A airplane (Army Serial No. 45-79488). The airplane developed a pitching-up tendency at approximately 0.80 Mach number which necessitated large push forces and down-elevator deflections for further increases in speed. In steady turns at 35,000 feet with the center of gravity at 28.3 percent mean aerodynamic chord for normal accelerations up to the maximum test value, the control-force gradients were excessive at Mach numbers over 0.78. Airplane buffeting did not present a serious problem in accelerated or unaccelerated flight at 15,000 and 35,000 feet up to the maximum test Mach number of 0.84. It is believed that excessive control force would be the limiting factor in attaining speeds in excess of 0.84 Mach number, especially at altitudes below 35,000 feet.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8K03
    Format: application/pdf
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  • 95
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    Force- and Pressure-Distribution Measurements on Eight Fuselages (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The present report deals with force- and pressure-distribution measurements on a number of fuselage forms of varying slenderness ratio, varying rearward position of maximum thickness, and varying nose ratio. The effect of these parameters on the force and moment coefficients was determined. The linearity of the difference between the theoretical and experimental fuselage moments with the friction lift made it possible to indicate a neutral point and its travel with the different parameters. The pressure-distribution measurements yielded absolute values for the increase of velocity. A comparison with the theory indicated good agreement at small angles of attack, but considerable differences at greater angles of attack, where potential flow could no longer be assumed.
    Keywords: Aerodynamics
    Type: NACA-TM-1194
    Format: application/pdf
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  • 96
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    Investigation of the Flying Mock-Up of the Consolidated Vultee XP-92 Airplane in the Ames 40- by 80-Foot Wind Tunnel. Force and Moment Characteristics (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This report contains the results of the investigation of the aerodynamic characteristics of the flying mock-up of the Consolidated Vultee XP-92 airplane as conducted in the Ames 40- by 80-foot wind tunnel, Data are presented for test conditions which would give information as to the limits of stability and controllability, and also, the effect of Reynolds number. No analysis of the data has been made.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8B04
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  • 97
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    An Investigation of the Wing and the Wing-Fuselage Combination of a Full-Scale Model of the Republic XP-91 Airplane in the Ames 40-by 80-Foot Wing Tunnel (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests of a full-scale model of the Republic XP-91 airplane were conducted to determine the longitudinal and lateral characteristics of the wing alone and the wing-fuselage combination, the characteristics of the aileron, and the damping in roll af the wing alone. Various high-lift devices were investigated including trailing-edge split flaps and partial- and full-span leading-edge slats and Krueger-type nose flaps. Results of this investigation showed that a very significant gain in maximum lift could be achieved through use of the proper leading-edge device, The maximum lift coefficient of the model with split flaps and the original partial-span straight slats was only 1.2; whereas a value of approximately 1.8 was obtained by drooping the slat and extending it full span, Improvement in maximum lift of approximately the same amount resulted when a full-span nose flap was substituted for the original partial-span slat.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8F09
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  • 98
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    Flight Measurements of Flying Qualities of a P-47D-30 Airplane (AAF No. 43-3441) to Determine Longitudinal Stability and Control and Stalling Characteristics (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Flight tests have been made to determine the longitudinal stability and control and stalling characteristics of the P-47.E-30 airplane. The teat results show the airplane to be unstable stick free in any power-on condition even at the most forward center-of-gravity position tested. At the rearward center-of-gravity position tested the airplane also had neutral to negative stick-fixed stability with power on. The characteristics in accelerated flight were acceptable at the forward center-of-gravity position at low and high altitudes except at high speed where the control-force variations with acceleration were high. At the rearward center-of-gravity position, elevator-force reversals were experienced in turns at low speeds, and the force per g was low at all the other speeds. Ample stall warning was afforded in all the conditions tested and the stalling characteristics were very satisfactory except in the approach and wave-off conditions.
    Keywords: Aerodynamics
    Type: NACA-RM-L8A06
    Format: application/pdf
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  • 99
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    Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation to determine the performance and operational characteristics of an axial-flow gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet ram-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and corrected horsepower. For the range of corrected engine speeds investigated, overall total-pressure-loss ratio, cycle efficiency, and the fractional loss in cycle efficiency resulting from pressure losses in the combustion chambers were unaffected by a change in altitude or compressor-inlet ram-pressure ratio. For the range of corrected horsepowers investigated, the total-pressure-loss ratio and the fractional loss in cycle efficiency resulting from pressure losses in the combustion chambers decreased with an increase in corrected horsepower at a constant corrected engine speed. The combustion efficiency remained constant for the range of corrected horsepowers investigated at all corrected engine speeds.
    Keywords: Aerodynamics
    Type: NACA-RM-E8F10d
    Format: application/pdf
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  • 100
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    Wind-Tunnel Investigation of the Opening Characteristics, Drag, and Stability of Several Hemispherical Parachutes (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation has been conducted to determine the opening characteristics of several hemispherical parachutes and to study the influence of the parachute design variables on these opening characteristics. The effects of design variables on the drag and stability characteristics of the parachutes were also evaluated. The tests were made in the Langley 20-foot free-spinning tunnel and in the Langley 300 MPH 7 by 10-foot tunnel.
    Keywords: Aerodynamics
    Type: NACA-RM-L8J07a
    Format: application/pdf
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