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  • Weitere Quellen  (286)
  • Aerodynamics  (286)
  • 1950-1954  (76)
  • 1945-1949  (141)
  • 1940-1944  (69)
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  • Weitere Quellen  (286)
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  • 1
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    The Base Pressure at Supersonic Speeds on Two-Dimensional Airfoils and Bodies of Revolution (With and Without Fins) Having Turbulent Boundary Layers (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: An analysis has been made of available experimental data to show the effects of most variables that are predominant in determining base pressure at supersonic speeds. Two dimensional bases and bases of bodies of revolution, restricted to turbulent boundary layers, are covered.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L53C02
    Format: application/pdf
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  • 2
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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
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  • 3
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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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  • 4
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    Lift, Drag, and Pitching Moment of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds: Triangular Wing of Aspect Ratio 2 with NACA 0005-63 Thickness Distribution, Cambered and Twisted for a Trapezoidal Span Load Distribution (1951)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: A wing-body combination having a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, and twisted and cambered for a trapezoidal span load distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.60 to 0.90 and 1.30 to 1.70 at a Reynolds number of 3.0 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-A50K27a
    Format: application/pdf
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  • 5
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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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  • 6
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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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  • 7
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    The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack (1951)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: The subject of this paper is the drag of the nose section of bodies of revolution at zero angle of attack. The magnitude of the nose drag in relation to the total drag is very distinctly a function of the body design and the Mach number. It can range from a very small fraction of the total drag of the order of 10 percent to a very large fraction as high as 80 percent. The natural objective of nose design is to minimize the drag, but this objective is not always the primary one. Sometimes other factors overshadow the desire for minimum drag. The most conspicuous example of this is the proposal of guidance engineers that large-diameter spheres and other very blunt shapes be used at the nose tip. This paper will attempt to discuss both phases of the problem, noses for minimum drag and noses with very blunt tips. The state of the theory will also be reviewed and recent theoretical developments described, since the theory still remains a very valuable tool for assaying the effects of compromises in design and departure from shapes for which experimental data are available.
    Schlagwort(e): Aerodynamics
    Materialart: Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers; 1-12; NACA-RM-A51J25|NACA Conference on Aerodynamic Design Problems of Supersonic Guided Missiles; Oct 02, 1951 - Oct 03, 1951; Moffett Field, CA; United States
    Format: application/pdf
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  • 8
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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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  • 9
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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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  • 10
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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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