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  • Organic Chemistry  (475)
  • Industrial Chemistry  (296)
  • Aerodynamics  (21)
  • 550 - Earth sciences
  • 1945-1949  (792)
  • 1949  (792)
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  • 1945-1949  (792)
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  • 1
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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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  • 2
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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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  • 3
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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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  • 4
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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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  • 5
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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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  • 6
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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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  • 7
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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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  • 8
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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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  • 9
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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
    Format: application/pdf
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  • 10
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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
    Format: application/pdf
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