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  • Other Sources  (38)
  • Aerodynamics  (21)
  • Aircraft Propulsion and Power  (11)
  • Seismology  (6)
  • Cell & Developmental Biology
  • General Chemistry
  • LUNAR AND PLANETARY EXPLORATION
  • Limnology
  • 2020-2022
  • 1975-1979
  • 1945-1949  (38)
  • 1940-1944
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  • 1949  (38)
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  • 2020-2022
  • 1975-1979
  • 1945-1949  (38)
  • 1940-1944
  • 1920-1924
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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
    Publication Date: 1949
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 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
    Publication Date: 1949
    Keywords: Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 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
    Publication Date: 1949
    Keywords: NOISE ; Micro seismicity ; Seismology ; Meteorology ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Earthquake study in Southern California 1948 (1949)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 30, no. 6, pp. 595-597, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    In case of earthquake disaster (1949)
    American Red Cross, 2 pp.
    In:  Princeton, New Jersey, 7 + 273 pp., 1. ed., American Red Cross, 2 pp., vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; Earthquake precursor: prediction research
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Seismicity of the earth and associated phenomena (1949)
    Princeton Univ. Press
    In:  Princeton, New Jersey, 7 + 273 pp., 1. ed., Princeton Univ. Press, vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; Textbook of geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    High Speed Wind-Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 1/16-Scale Model of the D-558-2 Research Airplane at High Subsonic Mach Number and at a Mach Number of 1.2 (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-RM-L9C04
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  • 8
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    General Theory of Aerodynamic Instability and the Mechanism of Flutter (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom have been determined. The problem resolves itself into the solution of certain definite integrals, which have been identified as Bessel functions of the first and second kind and of zero and first order. The theory, being based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing-section theory relating to the steady case. The air forces being known, the mechanism of aerodynamic instability has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been arrived at. The solution is of a simple form and is expressed by means of an auxiliary parameter K.
    Keywords: Aerodynamics
    Type: NACA-TR-496
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  • 9
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    Boundary Layer Theory (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The purpose of this presentation is to give you a survey of a field of aerodynamics which has for a number of years been attracting an ever growing interest. The subject is the theory of flows with friction, and, within that field, particularly the theory of friction layers, or boundary layers. As you know, a great many considerations of aerodynamics are based on the so-called ideal fluid, that is, the frictionless incompressible fluid. By neglect of compressibility and friction the extensive mathematical theory of the ideal fluid (potential theory) has been made possible.
    Keywords: Aerodynamics
    Type: NACA-TM-1217
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  • 10
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    Wind-Tunnel Investigation of the Low-Speed Static Stability and Control Characteristics of a Model of Bell MX-776 (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley stability tunnel to determine the low-speed static stability and control characteristics of a model of the Bell MX-776. The results of the investigation indicated that the basic model configuration was longitudinally stable in the angle-of-attack range from about -16 deg. to 16 deg. but that the stability was a minimum near O deg angle of attack. The data indicated an aerodynamic-center position about 0.64 body diameters behind the center of gravity at low angles of attack. Reduction in the size of the front horizontal fins increased the longitudinal stability. With 20 percent of the span of the normal front horizontal fins cut off the aerodynamic center was about 1.04 body diameters behind the center of gravity, and with front horizontal fins having the same area as the front vertical fins, the aerodynamic center was 2.26 body diameters behind the center of gravity (at low angles of attack).
    Keywords: Aerodynamics
    Type: NACA-RM-SL9G08
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  • 11
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    Flight Investigations at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Fin-Stabilized Bodies of Revolution having Fineness Ratios of 12.5, 8.91, and 6.04 and Varying Positions of Maximum Diameter (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Rocket-powered models were flown at high-subsonic, transonic, and supersonic speeds to determine the zero-lift drag of fin-stabilized parabolic bodies of revolution differing in fineness ratio and in position of maximum diameter. The present paper presents the results for fineness ratio 12.5, 8.91 and 6.04 bodies having maximum diameters located at stations of 20, 40, 60, and 80 percent of body length. All configurations had cut-off sterns and all had equal base, frontal, and exposed fin areas. For most of the supersonic-speed range models having their maximum diameters at the 60-percent station gave the lowest values of drag coefficient. At supersonic speeds, increasing the fineness ratio generally reduced the drag coefficient for a given position of maximum diameter.
    Keywords: Aerodynamics
    Type: NACA-RM-L9I30
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  • 12
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    Altitude-Test-Chamber Investigation of Mcdonnell Afterburner on J34 Engine (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.00. Considerable difficulty was experienced in attempting to establish or maintain balanced-cycle engine operation at altitudes above 36,000 feet. The fuel-air ratio for balanced-cycle operation and lean blowout of the afterburner, the augmented-thrust ratio, the total specific fuel consumption, and the afterburner combustion efficiency for balanced-cycle operation are summarized in a table. Satisfactory afterburner ignition was obtained over a range of flight Mach Numbers from 0.32 to 0.60 at altitudes from 10,000 to 30,000 and engine speeds from 10,000 to 12,500 rpm.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9D19
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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
    Publication Date: 2019-07-12
    Description: A supersonic compressor design having supersonic velocity at the entrance of the stator is analyzed on the assumption of two-dimensional flow. The rotor and stator losses assumed in the analysis are based on the results of preliminary supersonic cascade tests. The results of the analysis show that compression ratios per stage of 6 to 10 can be obtained with adiabatic efficiency between 70 and 80 percent. Consideration is also given in the analysis to the starting, stability, and range of efficient performance of this type of compressor. The desirability of employing variable-geometry stators and adjustable inlet guide vanes is indicated. Although either supersonic or subsonic axial component of velocity at the stator entrance can be used, the cascade test results suggest that higher pressure recovery can be obtained if the axial component is supersonic.
    Keywords: Aerodynamics
    Type: NACA-RM-L9G06
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  • 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
    Publication Date: 2019-08-13
    Description: In the Institute for Flight Mechanics of the DVL a reactor arrangement with a maximum output of 100 kg was investigated as an expedient for the termination of dangerous spins on an airplane of the FW 56 type. reproduce the influence of a disturbance of the steady spin condition by a pitching or yawing moment. The tests were meant to reproduce the influence of a disturbance of the steady spin condition by a pitching and yawing moment.
    Keywords: Aerodynamics
    Type: NACA-TM-1221 , Zentrale fuer Wissenschaftliches Berichtswesen bei der Deutschen Versuchsanstalt fuer Luftfahrt Nr. 1027
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  • 15
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    Calculation of Counterrotating Propellers (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A method for calculation of a counterrotating propeller which is similar to Walchner's method for calculation of the single propeller in the free air stream is developed and compared with measurements. Several dimensions which are important for the design are given end simple formulas for the gain in efficiency derived. Finally a survey of the behavior of the propeller for various operating conditions is presented.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1208 , ZWB Forschungsbericht Nr. 1752
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  • 16
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    On Wind Tunnel Tests and Computations Concerning the Problem of Shrouded Propellers (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Results of measurements on a shrouded propeller are given. The propeller is designed for the high ratio of advance and high thrust loading. The effect of the shape of propeller and shroud upon the aerodynamic coefficients of the propulsion unit can be seen from the results. The highest efficiency measured is 0.71. The measurements permit the conclusion that the maximum efficiency can be essentially improved by shroud profiles of small chord and thickness. The largest static thrust factor of merit measured reaches according to Bendemann, a value of about zeta = 1.1. By the use of a nose split flap the static thrust for thin shroud profiles with small nose radius can be about doubled. In a separate section numerical investigations of the behavior of shrouded propellers for the ideal case and for the case with energy losses are carried out. The calculations are based on the assumption that the slipstream cross section depends solely on the shape of the shroud and not on the propeller loading. The reliability of this hypothesis is confirmed experimentally and by flow photographs for a shroud with small circulation. Calculation and test are also in good agreement concerning efficiency and static thrust factor of merit. The prospects of applicability for shrouded propellers and their essential advantages are discussed.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1202
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  • 17
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    Experimental study of flow past turbine blades (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The requirements on gas turbines for aircraft power units, namely, adequate efficiency, operation at high gas temperatures, low weight, and small dimensions, must be taken into consideration during the design of the blading. To secure good efficiency, it is necessary that the gas flow past the blades as smoothly as possible without separation. This is relatively easily obtainable in the accelerated flow of turbine blading, if the blade spacing is chosen small enough. A small blade spacing, however, is detrimental to the other requirements outlined above. Operation at high gas temperatures usually calls for blade cooling. This cooling is associated with a power input that lowers the turbine efficiency. Since the amount of heat that must be carried off for coding a blade can be influenced rather little, the gross power input for a turbine stage can be reduced by keeping the number of blades to a minimum, that is, with blades of high spacing ratio. But here also a limit is imposed, the exceeding of which is followed by separation of flow. Hence the requirement of finding blade forms on which the flow separates at rather high spacing ratios .
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1209
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  • 18
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    Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted to determine the performance characteristics of the rotor and inlet guide vanes used in the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. Outlet stators used in the engine were omitted to facilitate study of the supersonic rotor. The extent of the deviation from design performance indicates that the design-shock configuration was not obtained. A maximum pressure ratio of 2.26 was obtained at an equivalent tip speed of 1614 feet per second and an adiabatic efficiency of 0.61. The maximum efficiency obtained was 0.79 at an equivalent tip speed of 801 feet per second and a pressure ratio of 1.29. The performance obtained was considerably below design performance. The effective aerodynamic forces encountered appeared to be large enough to cause considerable damage to the thin aluminum leading edges of the rotor blades.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9G19
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  • 19
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    Performance of J33-A-21 and J33-A-23 Turbojet-Engine Compressors with Water Injection (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: As part of the performance investigation of compressors for the J33 turbojet engine, the A-21 model and the A-23 model with a 17- and a 34-blade impeller were operated with water injection at their respective design equivalent speeds of 11,500 and 11,750 rpm. Inlet conditions of pressure of 14 inches of mercury absolute and of ambient temperature correspond to those of the investigation of these models without water injection. The water-air ratio by weight ranged from 0.05 to 0.06. By the use of water injection, the peak pressure ratio of the A-21 compressor and the A-23 compressor with a 34-blade impeller increased approximately 0.38, whereas that of the A-23 compressor with a 17-blade impeller increased only 0.14. The decrease in maximum efficiency for the three compressors ranged from 0.12 to 0.14. The highest increase in maximum equivalent weight flow of air plus weight flow of water was 10.90 pounds per second obtained with the A-21 compressor. The increase in air weight flow alone was approximately 5.70 pounds per second for the A-21 compressor end the A-23, 17-blade compressor, which exceeded the increase of 3.15 pounds per second for the A-23; 34-blade compressor.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9G13
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  • 20
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    Jet Diffusion in Proximity of a Wall (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: When auxiliary jet engines are installed on airframes; as well as in some new designs, the jet engines are mounted in such a way that the jet stream exhausts in close proximity to the fuselage. This report deals with the behavior of the jet in close proximity to a two-dimensional surface. The experiments were made to find out whether the axially symmetric stream tends to approach the flat surface. This report is the last of a series of four partial test reports of the Goettingen program for the installation of jet engines, dated October 12, 1943. This report is the complement of the report on intake in close proximity to a wall.
    Keywords: Aerodynamics
    Type: NACA-TM-1214 , Untersuchungen und Mitteilungen; 3057
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  • 21
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    The Compressible Flow Past Various Plane Profiles Near Sonic Velocity (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In an earlier report UM No.1117 by Gothert,the single-source method was applied to the compressible flow around circles, ellipses, lunes, and around an elongated body of revolution at different Mach numbers and the results compared as far as possible with the calculations by Lamla ad Busemann. Essentially, it was found that with favorable source arrangement the single-source method is in good agreement with the calculations of the same degree of approximation by.Lamla and Busemann. Near sonic velocity the number of steps must be increased considerably in order to sufficiently approximate the adiabatic curve. After exceeding a certain Mach number where local supersonic fields occur already, it was no longer possible, in spite of the substantially increased number of steps, to obtain a systematic solution because the calculation diverged. This result,was interpreted to mean that above this point of divergence the symmetrical type of flow ceases to exist and changes into the unsymmetrical type characterized by compressibility shocks.
    Keywords: Aerodynamics
    Type: NACA-TM-1203 , Untersuchungen und Mitteilurgen; 1471
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  • 22
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    Effect of the Acceleration of Elongated Bodies of Revolution Upon the Resistance in a Compressible Flow (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The problem of the motion of an elongated body of revolution in an incompressible fluid may, as is known, be solved approximately with the aid of the distribution of sources along the axis of the body. In determining the velocity field, the question of whether the body moves uniformly or with an acceleration is no factor in the problem. The presence of acceleration must be taken into account in determining the pressures acting on the body. The resistance of the body arising from the accelerated motion may be computed either directly on the basis of these pressures or with the aid of the so-called associated masses (inertia coefficients). A different condition holds in the case of the motion of bodies in a compressible gas. In this case the finite velocity of sound must be taken into account.
    Keywords: Aerodynamics
    Type: NACA-TM-1230 , Prikladnaya Matematika I Mekhanika; 10; 4; 521-524
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  • 23
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    An Approximate Method for Calculation of the Laminar Boundary Layer with Suction for Bodies of Arbitrary Shape (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Various ways were tried recently to decrease the friction drag of a body in a flow; they all employ influencing the boundary layer. One of them consists in keeping the boundary layer Laminar by suction; promising tests have been carried out. Since for large Reynolds numbers the friction drag of the laminar boundary layer is much lower than that of the turbulent boundary layer, a considerable saving in drag results from keeping the boundary layer laminar, even with the blower power required for suction taken into account. The boundary layer is kept laminar by suction in two ways: first, by reduction of the thickness of the boundary layer and second, by the fact that the suction changes the form of the velocity distribution so that it becomes more stable, in a manner similar to the change by a pressure drop. There by the critical Reynolds number of the boundary layer (USigma*/V) (sub crit) becomes considerably higher than for the case without suction. This latter circumstance takes full effect only if continuous suction is applied which one might visualize realized through a porous wall. Thus the suction quantities required for keeping the boundary layer laminar become so small that the suction must be regarded as a very promising auxiliary means for drag reduction.
    Keywords: Aerodynamics
    Type: NACA-TM-1216
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  • 24
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    Systematic Investigations of the Effects of Plan Form and Gap between the Fixed Surface and Control Surface on Simple Flapped Wings (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Four component measurements of 12 wings of symmetric profile having flaps with chord ratios t(sub R)/t(sub L) = 0.3 and t(sub R)/t(sub L) = 0.2 are treated in this report. As a result of the investigations, the effects of plan form and gap between fixed surface and control surface have been clarified. Lift, drag, pitching moment, and hinge moment were measured in the control-surface deflection range: -23 deg 〈 or = beta 〈 or = 23 deg and the range of angle of attack: -20 deg 〈 or = alpha 〈 or = 20 deg. Six wings with flaps of small chord (t(sub R)/t(sub L) 〈 0.1) were investigated at large flap settings.
    Keywords: Aerodynamics
    Type: NACA-TM-1206 , ZWB Forschungsbericht; Rept-552/4
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  • 25
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    Flow Pattern in a Converging-Diverging Nozzle (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The present report describes a new method for the prediction of the flow pattern of a gas in the two-dimensional and axially symmetrical case. It is assumed that the expansion of the gas is adiabatic and the flow stationary. The several assumptions necessary of the nozzle shape effect, in general, no essential limitation on the conventional nozzles. The method is applicable throughout the entire speed range; the velocity of sound itself plays no singular part. The principal weight is placed on the treatment of the flow near the throat of a converging-diverging nozzle. For slender nozzles formulas are derived for the calculation of the velocity components as function of the location.
    Keywords: Aerodynamics
    Type: NACA-TM-1215 , Luftfahrtforschung; 91-102
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  • 26
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    Spin Investigation of a 1/29-Scale Model of the Republic XF-91 Airplane with a Conventional Tail Installed (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/29-scale model of the Republic XF-91 airplane with a.conventional-tail arrangement installed. Previously, tests were made on the model with a vee tail installed. The erect spin and recovery characteristics of the model were determined for the normal loading with the wing installed at various amounts of incidence. The spin investigation also included inverted-spin tests, spin-recovery-parachute tests, tests with the center of gravity moved rearward, and tests with external fuel tanks added to the model. In addition, several tail.modifications were tested,on the model in an attempt, to improve the model's spin-recovery characteristics. The results indicate that any fully developed spin obtained on the airplane with the conventional tail installed will be satisfactorily terminated if rudder reversal is accompanied by moving the ailerons with the spin (stick right in a right spin).Decreasing the wing incidence from 6deg to -2deg should have a beneficial effect on the recovery characteristics of the airplane. Recovery characteristics by normal use of controls (full rudder reversal followed by moving the elevators down) will be satisfactory if the wing incidence,of the airplane is -2deg. Installation of external fuel tanks (with or without fuel) will have a somewhat adverse effect on the recovery characteristics of the airplane, but if the recovery technique includes movement of the ailerons to full with the spin, the spin rotation will be terminated rapidly. Varying the position of the center of gravity within the limits indicated to be possible on the airplane should not affect the recovery characteristics.
    Keywords: Aerodynamics
    Type: NACA-RM-SL9E20
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  • 27
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    Two-Dimensional Wing Theory in the Supersonic Range (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The plane problem of the vibrating airfoil in supersonic flow is dealt with and solved within the scope of a linearized theory by the method of the acceleration potential.
    Keywords: Aerodynamics
    Type: NACA-TM-1238 , ZWB Forschungsbericht Nr. 1903; Rept-1903
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  • 28
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    Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzle designs in combination with special rotor blades having a 20 inlet angle. The performance is presented in terms of blade, rotor, and brake efficiency as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. The blade efficiency with the nozzle having circular pas- sages (K) was equal to or higher than that with the nozzle having rectangular passages (J) for all pressure ratios and speeds investigated. The maximum blade efficiency of 0.571 was obtained with nozzle K at a pressure ratio of 8 and a blade-jet speed ratio of 0.296. The difference in blade efficiency was negligible at a pressure ratio of 8 at the low speeds; the maxim difference was 0.040 at a pressure ratio of 20 and a blade-jet speed ratio of 0.260.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9H09
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  • 29
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    Performance of J33-A-27 Turbojet-Engine Compressor (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The J33-A-27 compressor was operated at an inlet pressure of 14 inches of mercury absolute and ambient inlet temperature over a range of equivalent impeller speeds from 6100 to 11,800 rpm. At the design equivalent speed of 11,800 rpm, the J33-A-27 compressor had a peak pressure ratio of 4.40 at an equivalent weight flow of 105.7 pounds per second and a peak adiabatic temperature-rise efficiency of 0.745. The maximum equivalent weight flow at design speed was 113.5 pounds per second.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9F30
    Format: application/pdf
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  • 30
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    Supplementary Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-2 Airplane (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A supplementary investigation on the stabilization of the Jettisonable nose section of the X-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. It was found that the nose section could be stabilized by the addition of curved fins which could be folded against the fuselage for normal flight.
    Keywords: Aerodynamics
    Type: NACA-RM-L9F22
    Format: application/pdf
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  • 31
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    Investigation in Simulated Vertical Descent of the Characteristics of a Cargo-Dropping Device having Extensible Rotating Blades (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The characteristics of a cargo-dropping device having extensible rotating blades as load-carrying surfaces have been studied in simulated vertical descent in the Langley 20-foot free-spinning tunnel. The investigation included tests to determine the variation in vertical sinking speed with load. A study of the blade characteristics and of the test results indicated a method of dynamically balancing the blades to permit proper functioning of the device.
    Keywords: Aerodynamics
    Type: NACA-RM-L9G14
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  • 32
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    Effect of Air Cooling of Turbine Disk on Power and Efficiency of Turbine from Turbo Engineering Corporation TT13-18 Turbosupercharger. (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was conducted to determine the effect of turbine-disk cooling with air on the efficiency and the power output of the radial-flow turbine from the Turbo Engineering Corporation TT13-18 turbosupercharger. The turbine was operated at a constant range of ratios of turbine-inlet total pressure to turbine-outlet static pressure of 1,5 and 2.0, turbine-inlet total pressure of 30 inches mercury absolute, turbine-inlet total temperature of 12000 to 20000 R, and rotor speeds of 6000 to 22,000 rpm, Over the normal operating range of the turbine, varying the corrected cooling-air weight flow from approximately 0,30 to 0.75 pound per second produced no measurable effect on the corrected turbine shaft horsepower or the turbine shaft adiabatic efficiency. Varying the turbine-inlet total temperature from 12000 to 20000 R caused no measurable change in the corrected cooling-air weight flow. Calculations indicated that the cooling-air pumping power in the disk passages was small and was within the limits of the accuracy of the power measurements. For high turbine power output, the power loss to the compressor for compressing the cooling air was approximately 3 percent of the total turbine shaft horsepower.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9E20
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  • 33
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    Performance of Axial-Flow Supersonic Compressor on XJ-55-FF-1 Turbojet Engine. I - Preliminary Performance of Compressor (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ-55-FF-1 turbo Jet engine. The test unit consisted of a row of inlet guide vanes and a supersonic rotor; the stator vanes after the rotor were omitted. The maximum pressure ratio produced in the single stage was 2.28 at an equivalent tip speed or 1814 feet per second with an adiabatic efficiency of approximately 0.61, equivalent weight flow of 13.4 pounds per second. The maximum efficiency of 0.79 was obtained at an equivalent tip speed of 801 feet per second.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9A31
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  • 34
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    Rough-water Landings of a 0.1-Size Powered Dynamic Model of the XP5Y-1 Flying Boat with Two Types of Afterbody - Langley Tank Model 228 (TED No. NACA DE309) (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A 0.1-size powered dynamic model of a large, high-speed flying boat was landed in Langley tank no. 1 into oncoming waves 4 feet high (full size). The model was tested with two afterbodies of differing lengths (4.12 and 6.63 beams). The short afterbody had a constant angle of dead rise of 22.5deg and a keel angle of 6.5deg. The long afterbody had warped dead rise and a keel angle of 8.5deg. The vertical accelerations were slightly greater and the maximum angular accelerations and maxim= trims were slightly less for the model with the long afterbody than for the model with -the short afterbody. A wave length of 210 feet (full size) imposed the highest accelerations on the model with either the long or the short afterbody.
    Keywords: Aerodynamics
    Type: NACA-RM-SL9B09
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  • 35
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    Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine. II - Performance of Inlet Guide Vanes as Separate Component (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The inlet wide vanes for the supersonic compressor of the XJ55-FF-1 engine were studied as a separate component in order to determine the performance prior to installation in the compressor test rig. Turning angles approached design values, and increased approximately to through the inlet Mach number range from 0.30 to choke. A sharp break in turning angle was experienced when the choke condition was reached. The total-pressure loss through the guide vanes was approximately 1 percent for the unchoked conditions and from 5 to 6 percent when choked.
    Keywords: Aerodynamics
    Type: NACA-RM-SE9E03
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  • 36
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    Performance of Axial-Flow Supersonic Compressor of the XJ55-FF-1 Turbojet Engine. IV - Analysis of Compressor Operation over a Range of Equivalent Tip Speeds from 801 to 1614 Feet Per Second (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. An analysis of the performance of the rotor was made based on detailed flow measurements behind the rotor. The compressor apparently did not obtain the design normal-shock configuration in this investigation. A large redistribution of mass occurred toward the root of the rotor over the entire speed range; this condition was so acute at design speed that the tip sections were completely inoperative. The passage pressure recovery at maximum pressure ratio at 1614 feet per second varied from a maximum of 0.81 near the root to 0.53 near the tip, which indicated very poor efficiency of the flow process through the rotor. The results, however, indicated that the desired supersonic operation may be obtained by decreasing the effective contraction ratio of the rotor blade passage.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9J14
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  • 37
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    NACA Conference on Aerodynamic Problems of Transonic Airplane Design (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: During the past several years it has been necessary for aeronautical research workers to exert a good portion of their effort in developing the means for conducting research in the high-speed range. The transonic range particularly has presented a very acute problem because of the choking phenomena in wind tunnels at speeds close to the speed of sound. At the same time, the multiplicity of design problems for aircraft introduced by the peculiar flow problems of the transonic speed range has given rise to an enormous demand for detail design data. Substantial progress has been made, however, in developing the required research techniques and in supplying the demand for aerodynamic data required for design purposes. In meeting this demand, it has been necessary to resort to new techniques possessing such novel features that the results obtained have had to be viewed with caution. Furthermore, the kinds of measurements possible with these various techniques are so varied that the correlation of results obtained by different techniques generally becomes an indirect process that can only be accomplished in conjunction with the application of estimates of the extent to which the results of measurements by any given technique are modified by differences that are inherent in the techniques. Thus, in the establishment of the validity and applicability of data obtained by any given technique, direct comparisons between data from different sources are a supplement to but not a substitute for the detailed knowledge required of the characteristics of each technique and fundamental aerodynamic flow phenomena.
    Keywords: Aerodynamics
    Type: NASA-TM-X-56649 , NACA Conference on Aerodynamic Problems of Transonic Airplane Design; Sep 27, 1949 - Sep 29, 1949; Hampton, VA; United States
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  • 38
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    Exact Calculation of Laminar Boundary Layer in Longitudinal Flow over a Flat Plate with Homogeneous Suction (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Lately it has been proposed to reduce the friction drag of a body in a flow for the technically important large Reynolds numbers by the following expedient: the boundary layer, normally turbulent, is artificially kept laminar up to high Reynolds numbers by suction. The reduction in friction drag thus obtained is of the order of magnitude of 60 to 80 percent of the turbulent friction drag, since the latter, for large Reynolds numbers, is several times the laminar friction drag. In considering the idea mentioned one has first to consider whether suction is a possible means of keeping the boundary layer laminar. This question can be answered by a theoretical investigation of the stability of the laminar boundary layer with suction. A knowledge, as accurate as possible, of the velocity distribution in the laminar boundary layer with suction forms the starting point for the stability investigation. E. Schlichting recently gave a survey of the present state of calculation of the laminar boundary layer with suction.
    Keywords: Aerodynamics
    Type: NACA-TM-1205 , Schriften der Deutschen Akademie der Luftfahrtforschung; 8; 1
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