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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
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    BIBLIOGRAFIE SEISMOLOGIE
  • 2
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    Unexplained phases in seismograms (1949)
    In:  Bull. Seism. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 39, no. 6, pp. 79-92, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1949
    Schlagwort(e): Seismology ; BSSA
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    BIBLIOGRAFIE SEISMOLOGIE
  • 3
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    Microseisms and meteorology (1949)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 30, no. 6, pp. 169, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1949
    Schlagwort(e): NOISE ; Micro seismicity ; Seismology ; Meteorology ; EOS
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    BIBLIOGRAFIE SEISMOLOGIE
  • 4
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    Earthquake study in Southern California 1948 (1949)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 30, no. 6, pp. 595-597, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1949
    Schlagwort(e): Seismology ; Seismicity ; EOS
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    BIBLIOGRAFIE SEISMOLOGIE
  • 5
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    In case of earthquake disaster (1949)
    American Red Cross, 2 pp.
    In:  Princeton, New Jersey, 7 + 273 pp., 1. ed., American Red Cross, 2 pp., vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publikationsdatum: 1949
    Schlagwort(e): Seismology ; Seismicity ; Earthquake precursor: prediction research
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    BIBLIOGRAFIE SEISMOLOGIE
  • 6
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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
  • 7
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    Index of NACA Technical Publications: 1915-1949 (1949)
    In:  CASI
    Details
    Publikationsdatum: 2018-06-05
    Beschreibung: The Index of NACA Technical Publications covers reports issued from the date of origin of the Committee in 1915 until approximately September 1949. Because omissions were noted after publication of the Index issued in 1947, and since many new reports have been released since that time, it was decided to issue a new volume to supersede completely the 1947 Index, with supplements to be issued regularly in the future. Commencing with all publications issued after September 1, 1949, subject classifications were revised, the most important change involving the transfer of aircraft loads reports from the Aerodynamics classification to Structures. For those maintaining a file of NACA index cards, it is recommended that cards issued for reports dated prior to September 1, 1949 be removed from the file. This volume includes the same index information. Supplements covering periods following September 1, 1949, will be arranged according to the revised subject classifications. On the pages immediately following, the subject classifications are indexed in order of breakdown. There is included in the back of this volume an alphabetical arrangement of the subject classifications.
    Schlagwort(e): Aeronautics (General)
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  • 8
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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
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  • 9
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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
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  • 10
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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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  • 11
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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
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  • 12
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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
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  • 13
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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
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  • 14
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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
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  • 15
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    Investigation of the NACA 4-(5)(08)-03 Two-blade Propeller at Forward Mach Numbers to 0.925 (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: No abstract available
    Schlagwort(e): Aeronautics (General)
    Materialart: NACA-RM-L9G06a
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  • 16
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    Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Nozzles and Three Rotor-Blade Designs (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzles and three rotor-blade designs. The performance was evaluated in terms of brake, rotor, and blade efficiencies at pressure ratios of 8, 15 (design), and 20. The blade efficiencies with the two nozzles are compared with those obtained with four other nozzles previously investigated with the same three rotor-blade designs. Blade efficiency with the cast nozzle of rectangular cross section (J) was higher than that with the circular reamed nozzle (K) at all speeds and pressure ratios with a rotor having a 0.45-inch 17 degree-inlet-angle blades. The efficiencies for both these nozzles were generally low compared with those of the four other nozzles previously investigated in combination with this rotor. At pressure ratios of 15 and 20, the blade efficiencies with nozzle K and the two rotors with 0.40-inch blades having different inlet angles were higher than with the four other nozzles, but the efficiency with nozzle J was generally low. Increasing the blade inlet angle from 17 degrees to 20 degrees had little effect on turbine performance, whereas changing the blade length from 0.40 to 0.45 inch had a marked effect. Although a slight correlation of efficiency with nozzle size was noted for the rotor with 0.45-inch 17 degree-inlet-angle blades, no such effect was discernible ,for the two rotors with 0.40-inch blades.Losses in the supersonic air stream resulting from the complex flow path in the small air passages are probably a large percentage of the total losses, and apparently the effects of changing nozzle size and shape within the limits investigated are of secondary importance.
    Schlagwort(e): Aeronautics (General)
    Materialart: NACA-RM-SE9J25
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  • 17
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    Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: A Mark 25 torpedo power plant modified to operate as a single-stage turbine was investigated to determine the performance with two nozzle designs and a standard first-stage rotor having 0.40-inch blades with a 17O met-air angle. Both nozzles had smaller port cross-sectional areas than those nozzles of similar design, which were previously investigated. The performance of the two nozzles was compared on the basis of blade, rotor, and brake efficiencies as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. At pressure ratios of 15 and 20, the blade efficiency obtained with the nozzle having circular passages (K) was higher than that obtained with the nozzle having rectangular passages (J). At a pressure ratio of 8, the efficiencies obtained with the two nozzles were comparable for blade-jet speed ratios of less than 0.260. For blade-jet speed ratios exceeding this value, nozzle K yielded slightly higher efficiencies. The maximum blade efficiency of 0.569 was obtained with nozzle K at a pressure ratio of 8 and a blade-jet speed ratio of 0.295. At design speed and pressure ratio, nozzle K yielded a maximum blade efficiency of 0.534, an increase of 0.031 over that obtained with nozzle J. When the blade efficiencies of the two nozzles were compared with those of four other nozzles previously investigated, the maximum difference for the six nozzles with this rotor was 0.050. From, this comparison, no specific effect of nozzles size or shape on over-all performance was discernible.
    Schlagwort(e): Aeronautics (General)
    Materialart: NACA-RM-SE9H30
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  • 18
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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
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  • 19
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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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  • 20
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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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  • 21
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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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  • 22
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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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  • 23
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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
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  • 24
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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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  • 25
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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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  • 26
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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
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  • 27
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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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  • 28
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    Comparison of Water-Load Distributions Obtained during Seaplane Landings with Bureau of Aeronautics Specifications. TED No. NACA 2413 (1949)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Bureau of Aeronautics Design Specifications SS-IC-2 for water loads in sheltered water are compared with experimental water loads obtained during a full--scale landing investigation. This investigation was conducted with a JRS-1 flying boat which has a 20 degrees dead-rise V-bottom with a partial chine flare. The range of landing conditions included airspeeds between 88 and 126 feet per second, sinking speeds between 1.6 and 9.1 feet per second, flight angles less than 6 degrees, and trims between 2 degrees and 12 degrees. Landings were moderate and were made in calm water. Measurements were obtained of maximum over-all loads, maximum pitching moments, and pressure distributions. Maximum experimental loads include over-all load factors of 2g, moments of 128,000 pound-feet, and maximum local pressures greater than 40 pounds per square inch. Experimental over-all loads are approximately one-half the design values, while local pressures are of the same order as or larger than pressures calculated from specifications for plating, stringer, floor, and frame design. The value of this comparison is limited, to some extent, by the moderate conditions of the test and by the necessary simplifying assumptions used in comparing the specifications with the experimental loads.
    Schlagwort(e): Aeronautics (General)
    Materialart: NACA-RM-SL9G01
    Format: application/pdf
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  • 29
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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
    Format: application/pdf
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  • 30
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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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  • 31
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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
    Format: application/pdf
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  • 32
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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
    Format: application/pdf
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  • 33
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    Neue Methoden zur Bestimmung der Herdtiefe von Erdbeben (1923)
    In:  Zeitschrift für angewandte Geophysik, New York, Am. Soc. Mech. Eng., vol. 1, no. 3, pp. 65-75, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1923
    Schlagwort(e): Hypocentral depth ; Seismology ; Review article
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    BIBLIOGRAFIE SEISMOLOGIE
  • 34
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    Brandung und Bodenunruhe II (1923)
    In:  Annalen der Hydrographie, New York, Am. Soc. Mech. Eng., vol. 51, no. 3, pp. 287-290, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1923
    Schlagwort(e): NOISE ; Seismology
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 35
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    Absorption und Fortpflanzungsgeschwindigkeit von seismischen Oberflächenwellen (1923)
    In:  Physikalische Zeitschrift, New York, Am. Soc. Mech. Eng., vol. 24, no. 3, pp. 458-459, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1923
    Schlagwort(e): Waves ; Seismology ; Surface waves ; Absorption
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  • 36
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    Theorie der Erdbebenwellen und verwandter Erscheinungen (1923)
    Gustav Fischer
    In:  Professional Paper, Erdbebenkunde, Jena, Gustav Fischer, vol. 65, no. VIIa, pp. 283-372, (ISBN: 3-540-23712-7)
    Details
    Publikationsdatum: 1923
    Schlagwort(e): Seismology ; Waves ; Elasticity
    Standort Signatur Erwartet Verfügbarkeit
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  • 37
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    Über den Erdkern in 2900 km Tiefe und die an ihm stattfindenden Reflexionen und Brechungen von Erdbebenwellen (1923)
    In:  Zeitschrift für angewandte Geophysik, New York, Am. Soc. Mech. Eng., vol. 1, no. 3, pp. 105-115, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1923
    Schlagwort(e): earth Core ; ConvolutionR ; Seismology
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  • 38
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    Die elastischen Konstanten im Erdinnern (1923)
    In:  Physikalische Zeitschrift, New York, Am. Soc. Mech. Eng., vol. 24, no. 3, pp. 296-299, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1923
    Schlagwort(e): Earth model, also for more shallow analyses ! ; Seismology
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 39
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    Theoretisches über Seismometer, Theoretisches über Registriervorrichtungen und Bestimmung von Konstanten von Seismometern (1923)
    Gustav Fischer
    In:  Professional Paper, Erdbebenkunde, Jena, Gustav Fischer, vol. 65, no. VIIa, pp. 450-477, (ISBN: 3-540-23712-7)
    Details
    Publikationsdatum: 1923
    Schlagwort(e): Seismology ; Instruments ; Seismometer
    Standort Signatur Erwartet Verfügbarkeit
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  • 40
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    The Minimum Induced Drag of Aerofoils (1923)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report helps explain the phenomenon of flight. It contains some theorems concerning the arrangement of airplane wings which are of considerable practical interest. In particular, it shows the theoretical reasons for the decrease of drag which accompanies all increase in the aspect ratio or lateral extension of a wing. The efficiency of a given arrangement of wings may be calculated from the formulae derived in this paper.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TR-121
    Format: application/pdf
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  • 41
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    Applications of Modern Hydrodynamics to Aeronautics (1923)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The report gives, rather briefly, in part one an introduction to hydrodynamics which is designed to give those who have not yet been actively concerned with this science such a grasp of the theoretical underlying principles that they can follow the subsequent developments. In part two there follows a separate discussion of the different questions to be considered, in which the theory of aerofoils claims the greatest portion of the space. The last part is devoted to the application of the aerofoil theory to screw propellers. A table giving the most important quantities is at the end of the report. A short reference list of the literature on the subject and also a table of contents are added.
    Schlagwort(e): Aeronautics (General)
    Materialart: NACA-TR-116
    Format: application/pdf
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