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  • Weitere Quellen  (142)
  • Aerodynamics  (76)
  • Aircraft Stability and Control  (47)
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  • 1
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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
    Publikationsdatum: 1949
    Schlagwort(e): Earthquake catalog ; Seismology ; Seismicity
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 2
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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
    Publikationsdatum: 1949
    Schlagwort(e): Seismology ; Seismicity ; EOS
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 3
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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
    Publikationsdatum: 1949
    Schlagwort(e): Seismology ; Seismicity ; Earthquake precursor: prediction research
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 4
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    Bemerkenswerte Schädlingsmeldungen (IV) (1949)
    In:  Ztschr. hyg. Zool. 37; p.317-320
    Details
    Publikationsdatum: 1949
    Beschreibung: 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:
    Schlagwort(e): Baden-Württemberg ; 1947-1949 ; Forst ; Pflanzenschädling
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 5
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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
    Publikationsdatum: 1949
    Beschreibung: 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:
    Schlagwort(e): Breisgau, Freiburg ; 1943-1944 ; Luftfeuchte ; Pflanzenschädling ; Temperatur ; Wein
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 6
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    Frittfliegenbefall in den Ähren der Wintergerste (1949)
    In:  Neue Mitt. Landwirtsch. 4; p.130-132
    Details
    Publikationsdatum: 1949
    Beschreibung: 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:
    Schlagwort(e): Deutschland ; 1948 ; Getreide ; Pflanzenschädling ; Gerste
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 7
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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
    Publikationsdatum: 1949
    Beschreibung: 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 -
    Schlagwort(e): Baden ; 1947 - 1948 ; Kartoffeln ; Niederschlag ; Pflanzenschädling
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 8
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    Zur Biologie und Bekämpfung des Pflaumenwicklers (Laspeyresia funebrana Tr.) in Norddeutschland (1949)
    In:  Anz. Schädlingskunde, p. 40-43
    Details
    Publikationsdatum: 1949
    Beschreibung: Beschreibende Beobachtungen zu den Generationen und zur Eiablage des Pflaumenwicklers sowie zur Bekämpfung mittels Spritzungen KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Schlagwort(e): Norddeutschland ; 1938/39 u. 1945-1947 ; Pflanzenschädling
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 9
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    Wie überwintert die grüne Pfirsichblattlaus? (1949)
    In:  Neue Mitt. Landwirtsch. 4; p.153-154
    Details
    Publikationsdatum: 1949
    Beschreibung: 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:
    Schlagwort(e): Labor ; 1943-1948 ; Pflanzenschädling ; Obst
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 10
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    Unbekannt
    Überwinterung der Pfirsichblattlaus (Myzodes persicae) im Winter 1948/1949 (1949)
    In:  Nachr.-Bl. Biol. Ztr.-Anstalt Braunschweig, p. 82
    Details
    Publikationsdatum: 1949
    Beschreibung: Verbale Beobachtungen zur Freilandüberwinterung der grünen Pfirsichblattlaus KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Schlagwort(e): Niedersachsen ; 1948-1949 ; Pflanzenschädling
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 11
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    Ein Auftreten des Zuckerrübenrüsslers (Tanymecus palliatus F.) an Spinat (1949)
    In:  Nachr. Bl. Biolog. Ztr.-Anst. Braunschweig, p.19
    Details
    Publikationsdatum: 1949
    Beschreibung: 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
    Schlagwort(e): Deutschland ; 1947-1948 ; Zuckerrüben ; Pflanzenschädling ; Temperatur ; Trockenheit ; Witterung ; Gemüse
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 12
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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
    Publikationsdatum: 1949
    Schlagwort(e): Seismology ; Seismicity ; Textbook of geophysics
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    BIBLIOGRAFIE SEISMOLOGIE
  • 13
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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
    Publikationsdatum: 2019-06-28
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L9C04
    Format: application/pdf
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  • 14
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    General Theory of Aerodynamic Instability and the Mechanism of Flutter (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TR-496
    Format: application/pdf
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  • 15
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    Boundary Layer Theory (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1217
    Format: application/pdf
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  • 16
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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).
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL9G08
    Format: application/pdf
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  • 17
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-SL9H31
    Format: application/pdf
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  • 18
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    Rotation in Free Fall of Rectangular Wings of Elongated Shape (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TM-1201 , Scientifiques et Techniques du Secretariat d'Etat a l'Aviation; Rept-178
    Format: application/pdf
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  • 19
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L9I30
    Format: application/pdf
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  • 20
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    Spin and Recovery Characteristics of the Northrop XF-89 Airplane (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-SL9B28a
    Format: application/pdf
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  • 21
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    Preliminary Analysis of Axial-Flow Compressors Having Supersonic Velocity at the Entrance of the Stator (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L9G06
    Format: application/pdf
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  • 22
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    Experimental Flights for Testing of a Reactor as an Expedient for the Termination of Dangerous Spins (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1221 , Zentrale fuer Wissenschaftliches Berichtswesen bei der Deutschen Versuchsanstalt fuer Luftfahrt Nr. 1027
    Format: application/pdf
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  • 23
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    Systematic model researches on the stability limits of the DVL series of float designs (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA/TM-1254
    Format: application/pdf
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  • 24
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-SL9I12
    Format: application/pdf
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  • 25
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA RM-SL52D23
    Format: application/pdf
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  • 26
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    Development of Spoiler Controls for Remote Control of Flying Missiles (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The present report deals with the aerodynamic, constructive, and instrumental development of a spoiler control for remote control of flying missiles.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TM-1210 , ZWB Forschungsbericht; Rept-1717
    Format: application/pdf
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  • 27
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    Jet Diffusion in Proximity of a Wall (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1214 , Untersuchungen und Mitteilungen; 3057
    Format: application/pdf
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  • 28
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    The Compressible Flow Past Various Plane Profiles Near Sonic Velocity (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1203 , Untersuchungen und Mitteilurgen; 1471
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  • 29
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    Effect of the Acceleration of Elongated Bodies of Revolution Upon the Resistance in a Compressible Flow (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1230 , Prikladnaya Matematika I Mekhanika; 10; 4; 521-524
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  • 30
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1216
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  • 31
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-Sl9G21A
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  • 32
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TM-1197 , ZWB Forschungsbericht Nr. 2000; Rept-2000
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  • 33
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1206 , ZWB Forschungsbericht; Rept-552/4
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  • 34
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    Flow Pattern in a Converging-Diverging Nozzle (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1215 , Luftfahrtforschung; 91-102
    Format: application/pdf
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  • 35
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL9E20
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  • 36
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    Two-Dimensional Wing Theory in the Supersonic Range (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1238 , ZWB Forschungsbericht Nr. 1903; Rept-1903
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  • 37
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    On the Motions of an Oscillating System Under the Influence of Flip-Flop Controls (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TM-1237 , ZWB Untersuchungen und Mitteilungen Nr. 1326; Rept-1326
    Format: application/pdf
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  • 38
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L9F22
    Format: application/pdf
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  • 39
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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
    Publikationsdatum: 2019-07-11
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L9G14
    Format: application/pdf
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  • 40
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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
    Publikationsdatum: 2019-07-12
    Beschreibung: 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).
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-SL9C28
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  • 41
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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
    Publikationsdatum: 2019-07-12
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL9B09
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  • 42
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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
    Publikationsdatum: 2019-07-12
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SE9E03
    Format: application/pdf
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  • 43
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    NACA Conference on Aerodynamic Problems of Transonic Airplane Design (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: 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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  • 44
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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
    Publikationsdatum: 2019-08-15
    Beschreibung: 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.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-SL9D21
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  • 45
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    Exact Calculation of Laminar Boundary Layer in Longitudinal Flow over a Flat Plate with Homogeneous Suction (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: 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.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1205 , Schriften der Deutschen Akademie der Luftfahrtforschung; 8; 1
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  • 46
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    Seismicity of the earth (1947)
    In:  Bull. Geol. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 58, no. 6, pp. 1252, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1947
    Schlagwort(e): Seismicity
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  • 47
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    Energy release in earthquakes (1947)
    In:  Bull. Geol. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 1266, no. 6, pp. 1252, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1947
    Schlagwort(e): Seismology ; Energy (of earthquakes) ; Seismicity
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  • 48
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    Larger shocks of 1946 (1947)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1946, no. 6, pp. 120, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1947
    Schlagwort(e): Seismology ; Earthquake catalog ; Seismicity
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  • 49
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    Earthquake study in Southern California 1946 (1947)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 28, no. 6, pp. 633-634, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1947
    Schlagwort(e): Seismology ; Seismicity ; EOS
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  • 50
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    Der Einfluss der Witterung auf den Massenwechsel des Rapserdflohs (Psylloides chrysocephala L.) (1947)
    In:  Nachrichten Blatt für den deutschen Pflanzenschutzdienst, p. 101-104
    Details
    Publikationsdatum: 1947
    Beschreibung: Beobachtungen zu den Witterungsverhältnissen im Winter 1946/47 und im Sommer 1947 und deren Auswirkungen auf den Rapserdfloh sowie ein Vergleich mit ähnlichen vergangenen Ereignissen KATASTER-BESCHREIBUNG: Zusammenhang zwischen Witterung (Temperatur und Niederschlag) und der Entwicklung des Rapserdflohs KATASTER-DETAIL: Delta T: T 〈 6°C, dann Eiablage; Delta T +, dann Schlüpfergebnis -; T 〉 30°C, dann keine Entwicklung von Larven Delta Nied -, dann Austrocknung der Eier +;
    Schlagwort(e): Mecklenburg, Thüringen, Sachsen, Brandenburg ; 1946-1947 ; Boden ; Niederschlag ; Pflanzenschädling ; Temperatur ; Trockenheit ; Witterung ; Raps
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  • 51
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    Stärkeres Auftreten des Kartoffelerdflohes (Psylloides affinis Payk.) in Mitteldeutschland (1947)
    In:  Nachrichtenblatt des deutschen Pflanzenschutzdienstes 1; p.105-109
    Details
    Publikationsdatum: 1947
    Beschreibung: Es wird über beobachtete Schwankungen im Auftreten des Kartoffelerdflohes im Zuge einer Temperaturerhöhung im Frühjahr 1947 berichtet. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Schlagwort(e): Sachsen-Anhalt, Thüringen ; 1947 ; Kartoffeln ; Pflanzenschädling ; Hackfrüchte
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  • 52
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    Untersuchungen über die Biologie und Bekämpfung der Obstbaumspinnmilbe Paratetranychus pilosus Can. et Fanz (1947)
    In:  Diss. Bonn, 118p.
    Details
    Publikationsdatum: 1947
    Beschreibung: Untersuchungen zur Entwicklung der Obstbaumspinnmilbe, ihrer Eiablage und ihres sonstigen Verhaltens unter natürlichen Umweltbedingungen KATASTER-BESCHREIBUNG: Zusammenhänge zwischen Temperatur und Niederschlag und der Anzahl und dem zeitlichen Vorkommen der Generationen sowie des Schlüpfens der Larven. KATASTER-DETAIL: Delta Nied +, dann Zeit für Entwicklung der Milben +; Delta T +, dann Zeit von Eiablage bis Schlüpfen -; Delta T + ,Delta Sonn + und/oder Delta Relf +, dann Anzahl schlüpfender Larven +; Delta T - und/oder Delta Nied +, dann Zeit für Entwicklung der Larven und Nymphen +; Delta T - und/oder Delta Nied +, dann Mortalität(Larven und Nymphen)+; Delta T + und Delta Relf -, dann Anzahl gelegter Sommereier +; Delta T +, dann Zeit für Entwicklung der Sommereier -; Delta T -, dann Anzahl gelegter Wintereier -; T 〈= 8°C, dann keine Eiablage; Delta Wind +, dann Anzahl abgewehter Milben +; Delta T (Frühjahr und Sommer) + und Delta Relf (Frühjahr und Sommer) -, dann starker Befall
    Schlagwort(e): Bergisches Land und Labor ; 1943-1944, 1946 ; Niederschlag ; Pflanzenschädling ; Temperatur ; Witterung ; Obst
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  • 53
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    Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L7J03
    Format: application/pdf
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  • 54
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    Investigation of Thrust Augmentation of a 1600-pound Thrust Centrifugal-flow-type Turbojet Engine by Injection of Refrigerants at Compressor Inlets (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Investigations were conducted to determine effectiveness of refrigerants in increasing thrust of turbojet engines. Mixtures of water an alcohol were injected for a range of total flows up to 2.2 lb/sec. Kerosene was injected into inlets covering a range of injected flows up to approximately 30% of normal engine fuel flow. Injection of 2.0 lb/sec of water alone produced an increase in thrust of 35.8% of rate engine conditions and kerosene produced a negligible increase in thrust. Carbon dioxide increased thrust 23.5 percent.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-E7G23
    Format: application/pdf
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  • 55
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    Experimental Investigation of a Preloaded Spring-tab Flutter Model (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An experimental investigation was made of a preloaded spring-tab flutter model to determine the effects on flutter speed of aspect ratio, tab frequency, and preloaded spring constant. The rudder was mass-balanced, and the flutter mode studied was essentially one of three degrees of freedom (fin bending coupled with rudder and tab oscillations). Inasmuch as the spring was preloaded, the tab-spring system was a nonlinear one. Frequency of the tab was the most significant parameter in this study, and an increase in flutter speed with increasing frequency is indicated. At a given frequency, the tab of high aspect ratio is shown to have a slightly lower flutter speed than the one of low aspect ratio. Because the frequency of the preloaded spring tab was found to vary radically with amplitude, the flutter speed decreased with increase in initial displacement of the tab.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L7G18
    Format: application/pdf
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  • 56
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    Observations on an Aileron-Flutter Instability Encountered on a 45 Degree Swept-Back Wing in Transonic and Supersonic Flight (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In the course of a flight test of a supersonic research pilotless aircraft (the NACA RM-1), large-amplitude aileron oscillations, probably aileron compressibility flutter, were encountered in the transonic and supersonic speed ranges. The wing was oscillating at the same frequency as the aileron. The aircraft was equipped with 45 degree swept-back wings of symmetrical NASA 65-010 airfoil section. Completely mass-balanced ailerons with 20 degree beveled trailing edges were installed on the wings. The ailerons were free floating with no mechanical restraining force other than the friction of the aileron hinges and servomechanism bearings throughout the high-speed interval of flight.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L6L09
    Format: application/pdf
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  • 57
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    High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees and 45 degrees of sweepback and sweepforward was made in a high-speed wind tunnel for aileron deflections from -10 degrees to 10 degrees and at Mach numbers from 0.60 to 0.96. Wing configurations of 30 degrees generally reduced the severity of the large changes in rolling-moment and aileron hinge-moment coefficients experienced by the upswept wing configurations as the result of compression shock and extended to higher Mach numbers the speeds at which such changes occurred.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L7I15
    Format: application/pdf
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  • 58
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    Low-Speed Wind-Tunnel Tests of a Pilotless Aircraft Having Horizontal and Vertical Wings and Cruciform Tail (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Low-speed tests of a pilotless aircraft were conducted in the Langley propeller-research tunnel to provide information for the estimation of the longitudinal stability and. control, to measure the aileron effectiveness, and to calibrate the radome and the Machmeter pitot-static orifices. It was found that the model possessed a stEb.le variation of elevator angle required for trim throughout the speed range at the design angle of attack. A comparison of the airplane with and without JATO units and with an alternate rocket booster showed that a large loss in longitudinal stability and control resulting from the addition of the rocket booster to the aircraft was sufficient to make the rocket-booster assembly unsatisfactory as an alternate for the JATO units. Reversal of the aileron effectiveness was evident at positive deflections of the vertical wing flap indicating that the roll-stabilization system would produce roiling moments in a tight right turn contrary to its design purpose. Vertical-wing-flap deflections caused large errors in the static-pressure reading obtained by the original static-tube installation. A practical installation point on the fuselage was located which should yield reliable measurement of the free-stream static pressure.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L6J18a
    Format: application/pdf
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  • 59
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    Calculations of the Supersonic Wave Drag of Nonlifting Wings with Arbitrary Sweepback and Aspect Ratio: Wings Swept Behind the Mach Lines (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: On the basis of a recently developed theory for finite sweptback wings at supersonic speeds, calculations of the supersonic wave drag at zero lift were made for a series of wings having thin symmetrical biconvex sections with untapered plan forms and various angles of sweepback and aspect ratios. The results are presented in a unified form so that a single chart permits the direct determination of the wave drag for this family of airfoils for an extensive range of aspect ratio and sweepback angle for stream Mach numbers up to a value corresponding to that at which the Mach line coincides with the wing leading edge. The calculations showed that in general the wave-drag coefficient decreased with increasing sweepback. At Mach numbers for which the Mach lines are appreciably ahead of the wing leading edge, the 'wave-drag coefficient decreased to an important extent with increases in aspect ratio or slenderness ratio. At Mach numbers for which the Mach lines approach the wing leading edge (Mach numbers approaching a value equal to the secant of the angle of sweepback), the wave-drag coefficient decreased with reductions in aspect ratio or slenderness ratio. In order to check the results obtained by the theory, a comparison was made with the results of tests at the Langley Memorial Aeronautical Laboratory of sweptback wing attached to a freely falling body. The variation of the drag with Mach number and aspect ratio as given by the theory appeared to be in reasonable
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L6K29
    Format: application/pdf
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  • 60
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    Measurements of Static and Total Pressure Throughout the Transonic Speed Range as Obtained from an Airspeed Head Mounted on a Freely Falling Body (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L7C04a
    Format: application/pdf
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  • 61
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    An Investigation of Convergent-Divergent Diffusers at Mach Number 1.85 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation has been conducted in the Cleveland 18- by 18-inch supersonic tunnel at a Mach number of 1.85 and angles of attack from 0 deg to 5 deg to determine optimum design configurations for a convergent-divergent type of supersonic diffuser with a subsonic diffuser of 5 deg included divergence angle. Total pressure recoveries in excess of theoretical recovery across a normal shock at a free-stream Mach number of 1.85 wore obtained with several configurations. The highest recovery for configurations without a cylindrical throat section was obtained with an inlet having an included convergence angle of 20 deg. Insertion of a 2-inch throat section between a 10 deg included angle inlet and the subsonic diffuser stabilized the shock inside the diffuser and resulted in recoveries as high as 0.838 free-stream total pressure at an angle of attack of 0 deg, corresponding to recovery of 92.4 percent of the kinetic energy of the free air stream. Use of the throat section also lessened the reduction in recovery of all configurations due to angle of attack.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-E6K21
    Format: application/pdf
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  • 62
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    Wind-Tunnel Investigation of Effects of Unsymmetrical Horizontal-Tail Arrangements on Power-on Static Longitudinal Stability of a Single-Engine Airplane Model (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A wind-tunnel investigation has been made to determine the effects of unsymmetrical horizontal-tail arrangements on the power-on static longitudinal stability of a single-engine single-rotation airplane model. Although the tests and analyses showed that extreme asymmetry in the horizontal tail indicated a reduction in power effects on longitudinal stability for single-engine single-rotation airplanes, the particular "practical" arrangement tested did not show marked improvement. Differences in average downwash between the normal tail arrangement and various other tail arrangements estimated from computed values of propeller-slipstream rotation agreed with values estimated from pitching-moment test data for the flaps-up condition (low thrust and torque) and disagreed for the flaps-down condition (high thrust and torque). This disagreement indicated the necessity for continued research to determine the characteristics of the slip-stream behind various propeller-fuselage-wing combinations. Out-of-trim lateral forces and moments of the unsymmetrical tail arrangements that were best from consideration of longitudinal stability were no greater than those of the normal tail arrangement.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TN-1474 , AD-A801528
    Format: application/pdf
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  • 63
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    Effects of Mach Number and Reynolds Number on the Maximum Lift Coefficient of a Wing of NACA 230-series Airfoil Sections (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps. Chordwise pressure-distribution measurements were made for all flap configurations.. Peak values of maximum lift coefficient were obtained at relatively low free-stream Mach numbers and, before critical Mach number was reached, were almost entirely dependent on Reynolds Number. Lift coefficient increased by increasing Mach number or deflecting flaps while critical pressure coefficient was reached at lower free-stream Mach numbers.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-1299
    Format: application/pdf
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  • 64
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    A Comparison of the Lateral Motion Calculated for Tailless and Conventional Airplanes (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Theoretical analysts of lateral dynamic motion of tailless and conventional airplanes was made for fighter and heavy transport. Their reactions to a lateral gust and control power required by each for simple maneuvers were determined and compared. Both types of airplanes require almost identical aileron control power to perform a given maneuver; tailless airplane requires about 1-2 to 1-3 directional control power of conventional airplane. Tailless airplane also shows greatest displacement for a given disturbance and has least damping in oscillatory mode.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-1154
    Format: application/pdf
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  • 65
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    Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-pipe Shrouds (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Investigations were made to develop a simplified method for designing exhaust-pipe shrouds to provide desired or maximum cooling of exhaust installations. Analysis of heat exchange and pressure drop of an adequate exhaust-pipe shroud system requires equations for predicting design temperatures and pressure drop on cooling air side of system. Present experiments derive such equations for usual straight annular exhaust-pipe shroud systems for both parallel flow and counter flow. Equations and methods presented are believed to be applicable under certain conditions to the design of shrouds for tail pipes of jet engines.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-1495
    Format: application/pdf
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  • 66
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    Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The first part of this paper reviews the present state of the problem of the instability of laminar boundary layers which has formed an important part of the general lectures by von Karman at the first and fourth Congresses and by Taylor at the fifth Congress. This problem may now be considered as essentially solved as the result of work completed since 1938. When the velocity fluctuations of the free-stream flow are less than 0.1 percent of the mean speed, instability occurs as described by the well-known Tollmien-Schlichting theory. The Tollmien-Schlichting waves were first observed experimentally by Schubauer and Skramstad in 1940. They devised methods of introducing controlled small disturbances and obtained measured values of frequency, damping, and wave length at various Reynolds numbers which agreed well with the theoretical results. Their experimental results were confirmed by Liepmann. Much theoretical work was done in Germany in extending the Tol1mien-Schlichting theory to other boundary conditions, in particular to flow along a porous wall to which suction is applied for removing part of the boundary layer. The second part of this paper summarizes the present state of knowledge of the mechanics of turbulent boundary layers, and of the methods now being used for fundamental studies of the turbulent fluctuations in turbulent boundary layers. A brief review is given of the semi-empirical method of approach as developed by Buri, Gruschwitz, Fediaevsky, and Kalikhman. In recent years the National Advisory.Commsittee for Aeronautics has sponsored a detailed study at the National Bureau of Standards of the turbulent fluctuations in a turbulent boundary layer under adverse pressure gradient sufficient to produce separation. The aims of this investigation and its present status are described.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-1168
    Format: application/pdf
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  • 67
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    Investigation of a Spoiler-Type Lateral Control System on a Wing with Full-Span Flaps in the Langley 19-Foot Pressure Tunnel (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Tests of a partial-span model of a large bomber-type air1ane were conducted to determine the. aerodynamic characteristics of the wing equipped with full-span flaps and a retractable spoiler end aileron lateral control system. The arrangement consisted of (1) a double slotted flap extending over aproximate1y 86 percent of the wing semispan, (2) a 20-percent constant-percentage-chord aileron extending from the outboard end of the flap to the wing tip, and (3) a retractable spoiler, located at the 65-percent wing-chord station and extending from approximately 63 percent of the wing semispan to the wing tip. In addition, tests were made of a wing vent (of 1 and 2 percent of the wing chord located directly behind the spoiler), perforations in the spoiler, a blot or cut-out along the lower edge of the spoiler and spoilers of various spans. With full-span flaps deflected and with the 2-percent vent open or closed the initial stalling of the wing occurred at the tips, but with the vents closed there probably would be no appreciable loss in lateral control until maximum lift was reached. The l-percent vent increased the rolling effectiveness of the spoiler at small spoi1er deflections, particularly at high angles of attack with flaps deflected. With flaps deflected the 2-percent vent caused a large reduction in both the wing lift and rolling effectiveness of the spoiler at large angles of attack. However, at small angle of attack the 2-percent vent increased the rolling effectiveness of the spoiler at small spoiler deflections. The simultaneous operation of the spoiler and vent (in contrast to a vent fixed in the wing) would result in a large increase in the effectiveness of the spoiler and would avoid any loss in wing lift as in a fixed vent arrangement. The tests of the spoiler modifications revealed that (1) the spoiler perforations reduced the rolling-moment and yawing-moment coefficients but caused the spoiler hinge-moment coefficients to become more positive; (2) the spoiler slot had no notable effect on the rolling-moment and yawing-moment characteristics but produced a positive increase in the spoiler hinge-moment coefficients at large spoiler deflections; (3) the effects produced by the individual modifications were additive when the various modifications were combined. In general, progressively decreasing the spoiler span by removing the segments from the inboard end of the spoiler caused a decrease in rolling effectiveness approximately proportional to the span of the segment.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TN-1409
    Format: application/pdf
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  • 68
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    Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1113 , Mitteilungen aus dem Institut fuer Aerodynamik an der Eidgenoessischen Technischen Hochschule; 10
    Format: application/pdf
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  • 69
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    Comparison of Wind-Tunnel Predictions with Flight Measurements of the Longitudinal-Stability and -Control Characteristics of a Douglas BTD-1 Airplane (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: Low Mach number longitudinal-stability and control characteristics as predicted by use of wind tunnel data from a powered 3/16-scale model are compared with flight test measurements of a Navy BTD-1 airplane. The accuracy of the wind tunnel data and the discrepancies involved in attempting to correlate with flight data are discussed and analyzed. The comparison showed that wind tunnel predictions were, in general, in good agreement with flight test data. The predicted values were for the most part sufficiently accurate to show the satisfactory and unsatisfactory characteristics in the preliminary design stage and to indicate possible methods of improvement. The discrepancies which did occur were attributed principally to physical dissimilarities between model and airplane and the instability to determine accurately the flight power conditions. The effect of Mach number was considered negligible since the maximum flight test value was about 0.5. In order to simulate more closely the flight conditions and hence obtain more accurate data for predictions, it appears desirable to perform large-scale tests of unorthodox control surfaces such as the sealed vaned elevators with which the airplane was equipped.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-A6L30
    Format: application/pdf
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    The Calculation of Compressible Flows with Local Regions of Supersonic Velocity (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: This report addresses a method for the approximate calculation of compressible flows about profiles with local regions of supersonic velocity. The flow around a slender profile is treated as an example.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1114 , Forschungsbericht-1794 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters
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  • 71
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    Hydrodynamic Qualities of a 1/10-Size Powered Dynamic Model of the XP5Y-1 Flying Boat in Smooth Water: Langley Tank Model 246, TED No. NACA DE 320 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The hydrodynamic characteristics of a 1/10-size powered dynamic model of the XP5Y-1 flying boat were determined in Langley tank no. 1. Stable take-offs were possible at all practicable positions of the center of gravity and flap deflections. An increase in gross load from 123.5 to 150.0 pounds (21.5 percent) had only a slight effect on the stable range for take-off. A decrease in forward acceleration from 3.0 to 1.0 feet per second per second had only a very small effect on the stable range for take-off. In general, the landings were free from skipping except at trims below 6 deg where one skip was encountered at an aft position of the center of gravity. The model porpoised during the landing runout at all positions of the center of gravity when landed at trims above 10 deg. Spray in the propellers was light at the design gross load, and was not considered excessive,at a gross load of 136.0 pounds.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-SL9K14
    Format: application/pdf
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  • 72
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    Preliminary Evaluation of the Low-Speed Stability and Control Characteristics of the McDonnell XP-85 Airplane from Tests of an Unballasted 1/5-Scale Model in the Langley Free-Flight Tunnel (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: At the request of the Air Material Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a jet propelled, parasite fighter with a 34 deg sweepback at the wing quarter chord. It was designed to be carried in a bomb bay of the B-36 air plane. The first portion of the investigation consists of a preliminary evaluation of the stability and control characteristics of the airplane from force and fight tests of an unballasted 1/5-scale model. The second portion of the investigation consists of test of a properly balasted 1/10-scale model which will include a study of the stability of the Xp-85 when attached to the trapeze for retraction into the B-36 bomb bay. The results of the preliminary test with the 1/5-scale model are presented herein. This portion fo the investigation included tests of the model with various center fin arrangements. Both the design nose flap and a stall control vane were investigated.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L7C27
    Format: application/pdf
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  • 73
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    Longitudinal Characteristics of a Semispan Model of the Grumman Airplane Design 83 having a Sweptback Wing and of the Model with a Straight Wing as Determined from Wing-Flow Tests at Transonic Speeds, TED No. NACA DE337 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation has been made by the NACA wing-flow method to provide information on the relative longitudinal characteristics of a straight and sweptback wing in the transonic speed range. Tests were made of a semispan model of the Grumman airplane design 83 (XFlOF) incorporating a wing swept back 42.5deg with reference to quarter-chord line and also of the model with the swept wing replaced by a straight wing similar to that of the XF9F airplane. The airfoil sections were symmetrical 64l-series, with thickness ratios of 12 percent for the straight wing and 10 percent for the sweptback wing parallel to the stream direction. Measurements were made of normal force, chord force, and pitching moment at various angles of attack with the two wings both with and without the empennage, and with the fuselage alone. The tests covered a range of effective Mach numbers at the wing of the model from 0.65 to 1.10.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL9A19
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  • 74
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    Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane with a Full-Span Leading-Edge Slat in the Langley Free-Flight Tunnel (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation of the low-speed; power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane equipped with full-span leading-edge slats has been conducted in the Langley free-flight tunnel. In this investigation it was found that the-full-span leading-edge slat gave about the same maximum lift coefficient as was obtained with the outboard single slotted flap and inboard slat. The stability and control characteristics were greatly improved except near the stall where the characteristics with the full-span slat were considered unsatisfactory because of a loss of directional stability and a slight nosing-up tendency.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-SL7L17
    Format: application/pdf
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  • 75
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    The Effectiveness at High Speeds of a 20-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An analysis has been made of the lift control effectiveness of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section from section lift-coefficient data obtained at Mach numbers from 0.3 to 0.875. In addition, the effectiveness of the plain flap as a lift-control device has been compared with the corresponding effectiveness of both a spoiler and a dive-recovery flap on the NACA 65-210 airfoil section. The analysis indicates that the plain trailing-edge flap employed on the 10-percent-thick airfoil at Mach numbers as high as 0.875 retains at least 50-percent of its low-speed lift-control effectiveness, and is sufficiently effective in lateral control application, assuming a rigid wing, to provide adequate airplane rolling characteristics. The plain trailing-edge flap, as compared to the spoiler and the dive-recovery flap, appears to afford the most favorable characteristics as a device for controlling lift continuously throughout the range of Mach numbers from 0.3 to 0.875. At Mach numbers above those for lift divergence of the wing, either a plain flap or a dive-recovery flap may be used on a thin airplane wing to provide auxiliary wing lift when the airplane is to be controlled in flight, other than in dives, at these Mach numbers. The choice of a lift-control device for this use, however, should include the consideration of other factors such as the increments of drag and pitching moment accompanying the use of the device, and the structural and high-speed aerodynamic characteristics of the airplane which is to employ the device.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-A7A17
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  • 76
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    Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: On the basis of a recently developed theory for sweptback wings at supersonic velocities, equations are derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Distributions of section wave drag along the span of tapered wings are, in general, very similar in shape to those of untapered plan forms. For a given taper ratio and aspect ratio, an appreciable reduction in wing wave-drag coefficient with increased sweepback is noted for the entire range of Mach number considered. For a given sweep and taper ratio, higher aspect ratios reduce the wing wave-drag coefficient at substantially subcritical supersonic Mach numbers. At Mach numbers approaching the critical value, that is, a value equal to the secant of the sweepback angle, the plan forms of low aspect ratio have lower drag coefficients. Calculations for wings of equal root bending stress (and hence different aspect ratio) indicate that tapering the wing reduces the wing wave-drag coefficient at Mach numbers considerably less than the critical value and a decrease of the drag coefficient with taper at Mach numbers near the critical value.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L7E23a
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  • 77
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    Force and Pressure-Distribution Measurements on a Rectangular Wing with Double-Hinged Nose (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The previous measurements on airfoils with hinged nose disclosed a comparatively large low-pressure peak at the bend of the hinged nose; which favored the separation of flow. It was therefore attempted to reduce these low-pressure peaks by reducing the camber of the forward profile and thereby ensure a longer adherence of the flow and a maximum lift increase. The forces were measured on a rectangular wing with double-hinged nose and end plates, the pressure distributions were measured in the center section of the wing. The measurements disclosed that the highest lift attained with a single-hinged nose cannot be increased by a double-hinged nose. The sum of the deflection angles of both hinged noses related to the maximum lift is about equal to the corresponding angle of the single-hinge nose (approx. 30 deg to 40). The respective angle of attack in both cases amounts to approx. 21 deg. Even the low-pressure peak is about the same in both cases (P/q approx. -5.5). Therefore, a milder curvature of the forward portion of the profile affords no definite increase of the maximum lift.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1117 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluft-zeugmeisters; Rept-1676/3
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  • 78
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    Calibration and Measurement in Turbulence Research by the Hot-Wire Method (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The problem of turbulence in aerodynamics is at present being attacked both theoretically and experimentally. In view of the fact however that purely theoretical considerations have not thus far led to satisfactory results the experimental treatment of the problem is of great importance. Among the different measuring procedures the hot wire methods are so far recognized as the most suitable for investigating the turbulence structure. The several disadvantages of these methods however, in particular those arising from the temperature lag of the wire can greatly impair the measurements and may easily render questionable the entire value of the experiment. The name turbulence is applied to that flow condition in which at any point of the stream the magnitude and direction of the velocity fluctuate arbitrarily about a well definable mean value. This fluctuation imparts a certain whirling characteristic to the flow.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TM-1130 , A Muegyetem Aerodinamikai Intezeteben Keszult Munka
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  • 79
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    Russian Laminar Flow Airfoils 3rd Part: Measurements on the Profile No. 2315 BIS with Ava-Nose Flap (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The tests on the Russian airfoil 2315 Bis were continued. This airfoil shows, according to Moscow tests, good laminar flow characteristics. Several tests were prepared in the large wind tunnel at Gottingen; partial results were obtained.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1127 , Untersuchungen und Mitteilungen; Rept-3067
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  • 80
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    Test Report on Three-and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Elliptic Wing) (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The report UM No. 1023/1 which presented the results of measurements for a series of trapezoidal wings was the beginning of a series on wings with aspect ratio 1 to 3 and various contours. In report No. 1023/1 the aspect ratio (Lambda = 4/3) remained the same; the tapering was modified. The present report gives the results of the series of elliptic wings. Here the aspect ratio varies from 1 to 2 with the sweepback. The contour is formed by elliptic arcs. The influence of sweepback and contour upon the neutral point is shown.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1146 , Untersuchungen und Mitteilungen; Rept-1023/3
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  • 81
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    Aerodynamic Characteristics at High Speeds of Full-Scale Propellers having Different Shank Designs (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Tests of two 10-foot-diameter two-blade propellers which differed only in shank design have been made in the Langley 16-foot high-speed tunnel. The propellers are designated by their blade design numbers, NACA 10-(5)(08)-03, which had aerodynamically efficient airfoil shank sections, and NACA l0-(5)(08)-03R which had thick cylindrical shank sections typical of conventiona1 blades, The propellers mere tested on a 2000-horsepower dynamometer through a range of blade-angles from 20deg to 55deg at various rotational speeds and at airspeeds up to 496 miles per hour. The resultant tip speeds obtained simulate actual flight conditions, and the variation of air-stream Mach number with advance ratio is within the range of full-scale constant-speed propeller operation. Both propellers were very efficient, the maximum envelope efficiency being approximately 0,95 for the NACA 10-(5)(08)-03 propeller and about 5 percent less for the NACA 10-(5)(08)-03R propeller. Based on constant power and rotational speed, the efficiency of the NACA 10-(05)(08)-03 propeller was from 2.8 to 12 percent higher than that of the NACA 10-(5)(08)-03R propeller over a range of airspeeds from 225 to 450 miles per hour. The loss in maximum efficiency at the design blade angle for the NACA 10-(5)(08)-03 and 10-(5)(08)-03R propellers vas about 22 and 25 percent, respectively, for an increase in helical tip Mach number from 0.70 to 1.14.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L6L27a
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  • 82
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    Effects of Variations in Forebody and Afterbody Dead Rise on the Resistance and Spray Characteristics of the 22ADR Class VPB Airplane: Langley Tank Model 207, TED No. NACA 2361 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation was made to determine the effects of changes in the amount and distribution of forebody and afterbody dead rise on the hydrodynamic resistance and spray characteristics of a 1/11-size model of the Bureau of Aeronautics design No. 22ADR class VPB airplane. The variations in dead rise within the range investigated had no significant effects on resistance or trim, free to trim, or on resistance or trimming moment, fixed in trim. The coordinates of the peaks of the bow-spray blisters, with reference to the model, were measured at low speeds, and it was found that the model with the low dead rise at the bow had the lowest blisters. The changes in position of the maximum dead rise of the afterbody had no effect on the bow-spray blister.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L7H18
    Format: application/pdf
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  • 83
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    An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel. Part V - Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage TED No. NACA DE308 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The wing-alone tests and the effect of the various vertical-fin modifications, speed-brake modifications, and fuselage modifications on the aerodynamic characteristics in pitch and yaw are presented in the present paper with a limited analysis of the results. Also included are tuft studies of the flow for some of the modifications tested.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L7J09
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  • 84
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    Theoretical Analysis and Bench Tests of a Control-Surface Booster Employing a Variable Displacement Hydraulic Pump (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The NACA is conducting a general investigation of servo-mechanisms for use in powering aircraft control surfaces. This paper presents a theoretical analysis and the results of bench tests of a control-booster system which employs a variable displacement hydraulic pump. The booster is intended for use in a flight investigation to determine the effects of various booster parameters on the handling qualities of airplanes. Such a flight investigation would aid in formulating specific requirements concerning the design of control boosters in general. Results of the theoretical analysis and the bench tests indicate that the subject booster is representative of types which show promise of satisfactory performance. The bench tests showed that the following desirable features were inherent in this booster system: (1) No lost motion or play in any part of the system; (2) no detectable lag between motion of the contra1 stick and control surface; and (3) Good agreement between control displacements and stick-force variations with no hysteresis in the stick-force characteristics. The final design configuration of this booster system showed no tendency to oscillate, overshoot, or have other undesirable transient characteristics common to boosters.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L6H30
    Format: application/pdf
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  • 85
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    Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane in the Langley Free-Flight Tunnel (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation of the low-speed, power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane has been conducted in the Langley free-flight tunnel. In the investigation it was found that with flaps neutral satisfactory flight behavior at low speeds was obtainable with an increase in height of the vertical tail and with the inboard slats opened. In the flap-down slat-open condition the longitudinal stability was satisfactory, but it was impossible to obtain satisfactory lateral-flight characteristics even with the increase in height of the vertical tail because of the negative effective dihedral, low directional stability, and large-adverse yawing moments of the ailerons.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L7J17
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  • 86
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 24, 1946 to August 6, 1946 at Orlando, Florida (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: The results obtained from gust and draft velocity measurements within thunderstorms for the period July 24, 1946 to August 6, 1946 at Orlando, Florida are presented herein. These data are summarized in tables I and II and are of the type presented in reference 1 for previous flights. In two thunderstorm traverses, indications of ambient-air temperature were obtained from photo-observer records. These data are summarized in table III.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L7C28
    Format: application/pdf
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  • 87
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    Wind-Tunnel Investigation of a 1/5-Scale Model of the Ryan XF2R Airplane (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Wind-tunnel tests on a 1/5-scale model of the Ryan XF2R airplane were conducted to determine the aerodynamic characteristics of the air intake for the front power plant, a General Electric TG-100 gas turbine, and to determine the stability and control characteristics of the airplane. The results indicated low-dynamic-pressure recover3- for the air intake to the TG-100 gas turbine ~rith the standard propeller in operation. Propeller cuffs were designed and tested for the purpose of imp~oving the dynamic-pressure recovery. Data obtained with the cuffs installed and the gap between the spinner an& the cuff sealed indicated a substantial gain in dynamic pressure recovery over that obtained with the standard propeller and with the cuffed propeller unsealed. Stability and control tests were conducted with the sealed cuffs installed on the propeller. The data from these tests indicated the following unsatisfactory characteristics for the airplane: 1. Marginal static longitudinal stability. 2. Inadequate directional stability and control. 3. Rudder-pedal-force reversal in the climb condition. 4. Negative dihedral effect in the power-on approach and wave-off conditions.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-Rm-SA7E26
    Format: application/pdf
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  • 88
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    Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of three deep-stepped planing-tail flying-boat hulls differing only in the amount of step fairing. The hulls were derived by increasing the unfaired step depth of a planing-tail hull of a previous aerodynamic investigation to a depth about 92 percent of the hull beam. Tests were also made on a transverse-stepped hull with an extended afterbody for the purpose of comparison and in order to extend and verify the results of a previous investigation. The investigation indicated that the extended afterbody hull had a minimum drag coefficient about the same as a conventional hull, 0.0066, and an angle-of-attack range for minimum drag coefficient of 0.0057 which was 14 percent less than the transverse stepped hull with extended afterbody; the hulls with step fairing had up to 44 percent less minimum drag coefficient than the transverse-stepped hull, or slightly more drag than a streamlined body having approximately the same length and volume. Longitudinal and lateral instability varied little with step fairing and was about the same as a conventional hull.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L7C18
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  • 89
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    On the Vortex Sound from Rotating Rods (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The motion of different bodies imersed in liquid or gaseous media is accompanied by characteristic sound which is excited by the formation of unstable surfaces of separation behind the body, usually disintegrating into a system of discrete vortices(such as the Karman vortex street due to the flow about an infintely long rod, etc.).In the noise from fans,pumps,and similar machtnery, vortexnQif3eI?Yequently predominates. The purpose of this work is to elucidate certain questions of the dependence ofthis sound upon the aerodynamic parameters and the tip speed of the rotating rods,or blades. Although scme material is given below,insufficientto calculate the first rough approximation to the solution of this question,such as the mechanics of vortex formation,never the less certain conclusions maybe found of practical application for the reduction of noise from rotating blades.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1136 , Zhurnal Tekhnicheskoi Fiziki; 14; 9; 561
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  • 90
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    Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Longitudinal-Stability and -Control Characteristics (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: This report contains the flight-test results of the longitudinal-stability and -control phase of a general flying qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). The tests were conducted at indicated airspeeds up to 530 miles per hour (0.76 Mach number) at low altitude and up to 350 miles per hour (0.82) Mach number) at high altitude. These tests showed that the flying qualities of the airplane were in accordance with the requirements of the Army Air Forces Stability and Control Specification except for excessive elevator control forces in maneuvering flight and the inadequacy of the longitudinal trimming control at low airspeeds.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-A7G01
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  • 91
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    Stick-Fixed Stability and Control Characteristics of the Consolidated Vultee Model 240 Airplane as Estimated from Tests of a 0.092-Scale Powered Model (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: Estimates of the static stick-fixed stability and control characteristics of the Consolidated Vultee model 240 airplane are presented in this report. The estimates are based on tests of a 0.092-scale powered model in the 10-foot wind tunnel of the Guggenheim Aeronautical Laboratory of the California Institute of Technology. Results of the analysis are evaluated in terms of the Army specifications for stability and control characteristics which are more specific and, in general, equal to or more rigid than the Civil Aeronautics Administration requirements. The stick-fixed stability and control characteristics of the Consolidated Vultee model 240 were found to be satisfactory except for the following: 1) Marginal longitudinal stability in the landing approach (flaps 30 deg, 50% minimum continuous power) with aft center of gravity (31% M.A.C.); 2) Marginal rudder control to hold zero sideslip in a climb after take-off with asymmetric power (flaps 30 deg, left engine inoperative, right engine delivering take-off power) with maximum rudder throw limited to +/- 18 deg; 3) Marginal dihedral effect with flaps 40 deg and engines delivering maximum continuous power.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-A7F19
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  • 92
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    High-Speed Aerodynamic Characteristics of a 1/7-Scale Model of the Northrop YB-49 Airplane (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: Tests were conducted to find the effects of compressibility on the longitudinal stability and control of a 1/7-scale semispan model of the Northrop YB-49 airplane. Lift, drag, pitching moment, and elevon hinge moments were measured and are presented in graphical form. The results show that, due to a loss of lift on the outboard portion of the wing, the longitudinal static stability decreased rapidly as the Mach numbers increased above 0.735 the model experienced a climbing moment at positive lift coefficients. Also, a longitudinal-control effectiveness began to decrease at a Mach number of about 0.725
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-A7C13
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  • 93
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    Systematic Wind-Tunnel Measurements on Missiles (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: Wind-tunnel measurements on projectiles are discussed. Tests at the Gottingen Tunnel are described. The tunnel operates on the Prandtl principle, that is, a brief stationary air stream produced in an evacuated tank by induction of atmospheric air.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TM-1122 , Lilienthal-Gesellschaft; 139; 29-37
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  • 94
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    The Separation of Flow Due to Compressibility Shock (1947)
    In:  CASI
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    Publikationsdatum: 2019-08-15
    Beschreibung: It is known that the compressibility shocks accompanying local or total supersonic flows lead to pronounced flow separations which result in unusually high energy losses on airplane wings, vanes, and in diffusers. These phenomena were investigated experimentally and theoretically.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1152 , Technische Berichte Band; 10; 2; 59-61
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  • 95
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    Calculations and Experimental Investigations on the Feed-Power Requirement of Airplanes with Boundary-Layer Control (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Calculations and test results are given about the feed-power requirement of airplanes with boundary-layer control. Curves and formulas for the rough estimate of pressure-loss and feed-power requirement are set up for the investigated arrangements which differ structurally and aerodynamically. According to these results the feed power for three different designs is calculated at the end of the report.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1167 , Deutsche Luftfahrtforschung, Forschungsbericht No. 1618
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  • 96
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    Lift and Drag of Wings with Small Span (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The lift coefficient of!a wing of small span at first shows a linear increase for the increasing angle of attack, but to a lesser degree then was to be expected according to the theory of the lifting line; thereafter the lift coefficient increases more rapidly than linearity, as contrasted with the the theory of the lifting line. The induced drag coefficient for a given lift coefficient, on the other hand, is obviously much smaller than it would be according to the theory. A mall change in the theory of the lifting line will cover these deviations.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-TM-1151 , Deutsche Luftfahrtforschung, Forschungsbericht; Rept-1665
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  • 97
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    An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel. Part I - Basic Longitudinal Stability Characteristics, TED No. NACA DE308 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane have been investigated over a Mach number range from 0.40 to 0.91. Results of the basic longitudinal tests of the complete model with undeflected control surfaces are given in the present report with a very limited analysis of the results.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L7G08-Pt-1
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  • 98
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    Longitudinal Stability and Control Characteristics of a Semispan Model of the XF7U-1 Tailless Airplane at Transonic Speeds by the NACA Wing-Flow Method, TED No. NACA DE307 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation was made by the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan model of the XF7U-1 tailless airplane. The 25-percent chord line of the wing of the model was swept back 35 deg. The airfoil sections of the wing perpendicular to the 25-percent chord line were 12 percent thick. Measurements were made of the normal force and pitching moment through an angle-of-attack range from about -3 deg to 14 deg for several ailavator deflections at Mach numbers from 0.65 to about 1.08. The results of the tests indicated no adverse effects of compressibility up to a Mach number of at least 0.85 at low normal-force coefficients and small ailavator deflections. Up to a Mach number of 0.85, the neutral point at low normal-force coefficients was at about 25 percent of the mean aerodynamic chord and moved rearward irregularly to 41 or 42 percent with a further increase in Mach number to about 1.05. For deflections up to -8.0 percent, the ailavator was effective in changing the pitching moment except at Mach numbers from 0.93 to about 1.0 where ineffectiveness or reversal was indicated for deflections and normal-force coefficients. With -13.2 deg deflection at normal-force coefficients above about 0.3, reversal of ailavator effectiveness occurred at Mach numbers as low as 0.81. A nose-down trim change, which began at a Mach number of about 0.85, together with the loss in effectiveness of the ailavator, indicated that with increase in the Mach number from about 0.95 to 1.05 an abrupt ailavator movement of 5 deg or 6 deg first up and then down would be required to maintain level flight.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L7I08
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 99
    facet.materialart.
    Unbekannt
    Tank Tests of a 1/7-Size Dynamic Model of the Grumman XJR2F-1 Amphibian to Determine the Effect of Slotted- and Split-Type Flaps on Take-Off Stability - NACA Model 212, TED No. NACA 2378 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Additional tests of a 1/7-size model of the Grumman XJR2F-1 amphibian were made in Langley tank no. 1 to compare the behavior during take-off of the model equipped with split- and slotted-type flaps. The slotted flag had a large effect on locating the forward center-of-gravity limits for stable take-offs. Stable take-offs within the normal operating range of positions of the center of gravity could be made with the split flaps deflected 45deg or with the slotted flaps deflected less than 20deg. At flap deflections required for similar take-off stability, the use of split-flaps resulted lower take-off speeds than the use of slotted flaps. An increase in forward acceleration from 1.1 to 4.8 feet per second per second moved the center-of-gravity limit forward approximately 3-percent mean aerodynamic chord.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L7A07
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 100
    facet.materialart.
    Unbekannt
    Wind-Tunnel Tests of a 1/4-Scale Model of the Naval Aircraft Factory Float-Wing Convoy Interceptor, TED No. NACA 2314 (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: A 1/4 - scale model of the Naval Aircraft Factory float-wing convoy interceptor was tested in the Langley 7-by 10-foot tunnel to determine the longitudinal and lateral stability characteristics. The model was tested in the presence of a ground board to determine the effect of simulating the ground on the longitudinal characteristics.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-L6J15
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
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