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  • 1
    Publication Date: 1968-01-01
    Print ISSN: 0031-9171
    Topics: Physics
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  • 2
    Publication Date: 1964-11-01
    Description: The effect of compressibility is included here in a study of wakes created in two-dimensional, steady, aligned-fields, magnetogasdynamic flow past obstacles. The gas is assumed to be viscous, resistive, and thermally conducting. With the Oseen type of approximation as well as the magnetogasdynamic boundary-layer approximation, a great simplification in the formulation of wakes results. The boundary-layer equations, although linearized, still retain the coupling between the velocity, the magnetic, and the temperature fields. The solution of the magnetogasdynamic wake, in general, is a superposition of three individual-wake components, each satisfying a diffusion type of equation. Only one of them is capable of extending upstream. Hence the wake picture is generally characterized by a conventional downstream wake with also the possibility of the existence of anupstream one. To be sure, the general features of the magnetogasdynamic wakes in aligned-fields flows are similar to those of an incompressible fluid; however, the flow now, instead of just being subalfvénic, must be subcritical for the upstream wake to occur. That is, the flow condition corresponding to the occurrence of the upstream wake is such that the sum of the square of the Mach number M∞ and the square of the Alfvén number A∞ is less than unity. Evidently it is the mechanism of magneto-sonic-wave propagation that modifies the transition of wakes from the Alfvénic point A∞ = 1 (for an incompressible fluid) to the subcritical are [Formula omited] in the Taniuti-Resler diagram. © 1964, Cambridge University Press. All rights reserved.
    Print ISSN: 0022-1120
    Electronic ISSN: 1469-7645
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
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  • 3
    Publication Date: 2011-08-17
    Description: This paper discusses nonlinear stress-wave propagation in a perfectly flexible string obeying a quasilinear (rate-dependent) constitutive equation. Wave speeds and compatibility relations valid along various families of characteristics were determined. It was shown that the compatibility relations associated with the transverse as well as the longitudinal waves readily yield a physical interpretation when they are expressed in suitable variables and in vector form. Coding based on the present information was completed for the machine solution of a class of mixed initial- and boundary-value problems of practical interest. Computer simulation of the stress-wave interaction in the 40-foot lanyard in the Arcas 'Rocoz' system during deployment was carried out using a stress-strain relation for nylon at the strain rate of 30/second. A method for estimating the maximum tension and strain in a string during the initial loading phase is proposed.
    Keywords: PHYSICS (GENERAL)
    Type: Journal of the Astronautical Sciences; 25; Jan
    Format: text
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  • 4
    Publication Date: 2019-06-28
    Description: Closed-form formulas are presented for the interference factors of a body in the presence of a wing at supersonic speeds, when a finite afterbody is introduced. In addition, formulas are obtained for those cases in which the base of the body is forward of the trailing edge of the exposed root chord. These formulas are shown to be valid, subject to the restrictions inherent in the formulation given by Pitts, Nielsen and Kaattari (1959).
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; June 198
    Format: text
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  • 5
    Publication Date: 2019-06-28
    Description: Closed-form formulas for the effects of finite afterbodies on the longitudinal center of pressure location in the presence of a wing at supersonic speeds are presented, along with solutions for the case of negative afterbodies. A double integral is developed for the case of subsonic and supersonic leading edges and no afterbody and full afterbody. Attention is also given to the full/infinite body case, noting that a proportional variation of the pitching moment with the lift is found.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Aug. 198
    Format: text
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  • 6
    Publication Date: 2019-06-28
    Description: The NASA/ASEE Summer Faculty Fellowship Program (Aeronautics and Research) conducted at the NASA Goddard Space Flight Center during the summer of 1982 is described. Abstracts of the Final Reports submitted by the Fellows detailing the results of their research are also presented.
    Keywords: SOCIAL SCIENCES (GENERAL)
    Type: NASA-TM-85158 , NAS 1.15:85158
    Format: application/pdf
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  • 7
    Publication Date: 2019-07-13
    Description: The present asymptotic theory for generalized incompressible two-dimensional steady flow in curved channels has been constructed in the limit when gas thickness approaches zero with its lateral dimensions fixed; successive asymptotic solution terms are analytically generated by quadratures. In the second part of this work, the curvature of the gap treated is arbitrary. It is established that each term in the series solution of velocity and pressure is the product of a scale factor and a universal shape functions. Various interaction modes between the volume rate-of-flow, curvature, and its variations, are identified and quantitatively characterized.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Heat Transfer and Fluid Mechanics Institute Meeting; Jun 01, 1989 - Jun 02, 1989; Sacramento, Ca; United States
    Format: text
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  • 8
    Publication Date: 2019-07-13
    Description: The paper outlines a Theoretical Aerodynamic Derivatives (TAD) computer program for computing the aerodynamics of sounding rockets. TAD outputs include normal force, pitching moment and rolling moment coefficient derivatives as well as center-of-pressure locations as a function of the flight Mach number. TAD is applicable to slender finned axisymmetric vehicles at small angles of attack in subsonic and supersonic flows. TAD improvement efforts include extending Mach number regions of applicability, improving accuracy, and replacement of some numerical integration algorithms with closed-form integrations. Key equations used in TAD are summarized and typical TAD outputs are illustrated for a second-stage Tomahawk configuration.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-0504 , Sounding Rocket Technology Conference; Mar 07, 1979 - Mar 09, 1979; Houston, TX
    Format: text
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