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Development of a three-dimensional supersonic inlet flow analysis

A Chicago Christian School And Life-training Center For The Disabled (Historical Series of the Reformed Church in America)

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Published by Administrator in National Aeronautics and Space Administration, Scientific and Technical Information Office

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    • National Aeronautics and Space Administration, Scientific and Technical Information Office


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      • January 1980--Cover.Includes bibliographical references.

        StatementNational Aeronautics and Space Administration, Scientific and Technical Information Office
        PublishersNational Aeronautics and Space Administration, Scientific and Technical Information Office
        Classifications
        LC Classifications1980
        The Physical Object
        Paginationxvi, 99 p. :
        Number of Pages55
        ID Numbers
        ISBN 10nodata
        Series
        1
        2NASA contractor report -- NASA CR-3218.
        3NASA contractor report -- 3218.

        nodata File Size: 3MB.


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Development of a three-dimensional supersonic inlet flow analysis by National Aeronautics and Space Administration, Scientific and Technical Information Office Download PDF EPUB FB2


When calculating the velocity, the motion of the fluid is neglected.

Flow simulation of a supersonic airplane with installed engine nacelle

One- dimensional flow; boundary layer is represented only by its average effect on flow properties. For the Mach 7 configurations maximum back pressure ratios of approximately 120 were measured, which is about 4 times the nominal operating pressure ratio. Because of this, only a little pressure rise is recorded, although it is expected to be of the same magnitude than in the other cases.

Since it is based on a 24-hour dietary recall, this variable may be particularly susceptible to measurement error induced by recall bias. See also: ISABE-93-7104 Nobel, T. Engine cooling system uses the relatively cool air from the compression system that bypasses the combustor via air system flow paths to cool the turbine nozzle guide vanes and blades to ensure acceptable metal temperatures at elevated gas temperatures.

In addition to the parameter studies, a more rigorous approach to the optimal design and control has been taken. In the bottom half, the flow structure is very much influenced by the shock from the fixed part of the cowl, and thus the influence of the lip position is not as distinct.

Also AIAA Paper 2010-0032 and NASA TM-2010-216744, July 2010. In this model, viscous effects in blade passages can also be calculated directly, which include the exchange of momentum between fluids and detailed viscous flow close to walls.

A symmetric supersonic flow pattern was observed at both supercritical and critical operating conditions of the present Y-shaped DSI. Compared to external compression, this method has, in general, less of an entropy increase, but the overall length required for the shock system is greater. The distribution of y to be used in the model, in this package, must be binomial, Gaussian, or Poisson.

The 3-D combustion processes become more complex compared to those identified in the premixed study due to the additional shock structures introduced from the injection method and associated mixing processes. Capabilities highlighted in this paper include the design and analysis of streamline-traced external-compression inlets, modeling of Development of a three-dimensional supersonic inlet flow analysis bleed, and the design and analysis of mixed-compression inlets.

This type of inlet was extensively examined by Holland both computationally and experimentally [8, 9]. : Computational parametric study of sidewall-compression scramjet inlet performance at Mach 10. Space is composed of three orthogonal dimensions, and time is represented as a fourth dimension, perpendicular to each of the spatial axes.