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  • Cell & Developmental Biology  (1.061)
  • Aerodynamics  (210)
  • 1945-1949  (593)
  • 1940-1944  (678)
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  • 1
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    Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1113 , Mitteilungen aus dem Institut fuer Aerodynamik an der Eidgenoessischen Technischen Hochschule; 10
    Format: application/pdf
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  • 2
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    Two-Dimensional Potential Flow Past an Ordinary Thick Wing Profile (1942)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: This report deals with the development of a method which gives a lucid and convenient solution of the flow conditions in the vicinity of a common, thick airfoil section wherein the thickness of the profile is taken into account. The method consists in making the airfoil the streamline in a parallel flow by disposing on its mean line certain source and vortex distributions the fields of which are superposed on the parallel flow. These distributions of singularities are secured for the generalized Karman-Trefftz profile by means of conformal transformation from the flow about a circle. Five different distribution functions are afforded for the density of superposition, which combine in a specified manner to the necessary distributions of singularity and represent a generalized Karman-Trefftz profile in parallel flow. For these profiles the speed for each of the five distributions is then computed independently of the angle of attack.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1023
    Format: application/pdf
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  • 3
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    On the Vortex Sound from Rotating Rods (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The motion of different bodies imersed in liquid or gaseous media is accompanied by characteristic sound which is excited by the formation of unstable surfaces of separation behind the body, usually disintegrating into a system of discrete vortices(such as the Karman vortex street due to the flow about an infintely long rod, etc.).In the noise from fans,pumps,and similar machtnery, vortexnQif3eI?Yequently predominates. The purpose of this work is to elucidate certain questions of the dependence ofthis sound upon the aerodynamic parameters and the tip speed of the rotating rods,or blades. Although scme material is given below,insufficientto calculate the first rough approximation to the solution of this question,such as the mechanics of vortex formation,never the less certain conclusions maybe found of practical application for the reduction of noise from rotating blades.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1136 , Zhurnal Tekhnicheskoi Fiziki; 14; 9; 561
    Format: application/pdf
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  • 4
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    High-Speed Aerodynamic Characteristics of a 1/7-Scale Model of the Northrop YB-49 Airplane (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: Tests were conducted to find the effects of compressibility on the longitudinal stability and control of a 1/7-scale semispan model of the Northrop YB-49 airplane. Lift, drag, pitching moment, and elevon hinge moments were measured and are presented in graphical form. The results show that, due to a loss of lift on the outboard portion of the wing, the longitudinal static stability decreased rapidly as the Mach numbers increased above 0.735 the model experienced a climbing moment at positive lift coefficients. Also, a longitudinal-control effectiveness began to decrease at a Mach number of about 0.725
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-A7C13
    Format: application/pdf
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  • 5
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    The Calculation of Compressible Flows with Local Regions of Supersonic Velocity (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: This report addresses a method for the approximate calculation of compressible flows about profiles with local regions of supersonic velocity. The flow around a slender profile is treated as an example.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1114 , Forschungsbericht-1794 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters
    Format: application/pdf
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  • 6
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    The Lift Distribution of Swept-Back Wings (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: Two procedures for calculating the lift distribution along the span are given in which a better account is taken of the distribution of circulation over te area than in the Prandtl lifting-line theory. The methods are also applicable to wing sweepback. Calculated results for the two methods were in agreement.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1120 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters; 1553
    Format: application/pdf
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  • 7
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    Planing of Watercraft (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: The present report deals with the processes accompanying the planing of a planing boat or a seaplane on water . The study is largely based upon theoretical investigations; mathematical problems and proofs are not discussed. To analyze theoreticaly actual planing processes, giving due consideration to all aspects of the problem, is probably not possible. The theories therefore treat various simple limiting cases, which in their entirety give a picture of the planing processes and enable the interpretation of the experimental results. The discussion is concerned with the stationary planing attitude: the boat planes at a constant speed V on an originally smooth surface.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1139 , Jahrbuch der Schiffbautechnik; 34; 205-227
    Format: application/pdf
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  • 8
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    Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was determined in investigations of the complete engine in the NACA Cleveland altitude wind tunnel. Characteristics are presented as functions of the total-pressure ratio across the turbine and of turbine speed and gas flow corrected to sea-level conditions. Three turbine nozzles of different areas were used to determine the area that gave optimum performance. Inasmuch as tail-pipe nozzles of different diameters were investigated in combination with the standard turbine nozzle, the effect of varying discharge conditions on turbine operation could be observed. The investigations covered a range of pressure attitudes from 5000 to 40,000 feet. The engine was investigated over the entire operable range of speeds at each altitude. At pressure altitude of 30,000 feet, the effect on turbine operation of varying the ram pressure ration over a range from 1.10 to 1.77 was evaluated. An altitude effect was apparent when turbine pressure ratio was plotted against corrected turbine speed but it was so slight as to be negligible insofar as the turbine efficiencies were concerned. A maximum turbine efficiency of slightly more than 82 percent was obtained with the configuration using the standard turbine nozzle and the low-flow compressor. This efficiency, which is somewhat lower than the actual turbine efficiency, is uncorrected for accessories drive power, bearing friction, tail-pipe pressure drop, compressor thermal radiation, and introduction of turbine-disk cooling air into the gas stream. Changes in the ram pressure ratio had a negligible effect on the turbine efficiency.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-E8F09d
    Format: application/pdf
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  • 9
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    The Separation of Flow Due to Compressibility Shock (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: It is known that the compressibility shocks accompanying local or total supersonic flows lead to pronounced flow separations which result in unusually high energy losses on airplane wings, vanes, and in diffusers. These phenomena were investigated experimentally and theoretically.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1152 , Technische Berichte Band; 10; 2; 59-61
    Format: application/pdf
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  • 10
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    Drag Reduction by Suction of the Boundary Layer Separated Behind Shock Wave Formation at High Mach Numbers (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: With an approach of the velocity of flight of a ship to the velocity of sound, there occurs a considerable increase of the drag. The reason for this must be found in the boundary layer separation caused by formation of shock waves. It will be endeavored to reduce the drag increase by suction of the boundary layer. Experimental results showed that drag increase may be considerably reduced by this method. It was, also, observed that, by suction, the position of shock waves can be altered to a considerable extent.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1168 , ZWB-1424
    Format: application/pdf
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