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Sunday, July 19, 2020 | History

3 edition of Mach 10 experimental database of a three-dimensional scramjet inlet flow field found in the catalog.

Mach 10 experimental database of a three-dimensional scramjet inlet flow field

Scott D. Holland

Mach 10 experimental database of a three-dimensional scramjet inlet flow field

by Scott D. Holland

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  • 1 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, Available from the National Technical Information Service in Hampton, Va, Springfield, VA .
Written in English

    Subjects:
  • Airplanes -- Scramjet engines,
  • Airplanes -- Ramjet engines -- Air intakes,
  • Aerodynamics, Hypersonic

  • Edition Notes

    StatementScott D. Holland.
    SeriesNASA technical memorandum -- 4648.
    ContributionsLangley Research Center.
    The Physical Object
    Pagination214 p. :
    Number of Pages214
    ID Numbers
    Open LibraryOL17141237M
    OCLC/WorldCa33230284

    Analysis of Hypersonic Flow Using Three Dimensional Navier-Stokes Equations. Uncertainty Quantification for a Scramjet Inlet Flow. View Section, Multifidelity Simulation of a Dual Mode Scramjet Compression System Using Coupled NPSS and Fluent Codes Preliminary Study of Reacting Flow Field in a Burner with Cap-Induced Premixing. Three different test cases are conducted to analyze different flow conditions: The circular bump for low and high speed inviscid flows and computational performance assessment, the two-dimensional VKI turbine guide vane for viscous flows and the the three-dimensional DLR high speed centrifual compressor validating the performance for rotating.

    Flow Field in Axial Turbines The flow field in an axial turbine is quite complex. Flow entering the first stage guide vanes are mainly laminar and is two-dimensional across most of the span. At the end walls the flow is three-dimensional resulting in a horseshoe vortex formed by the interaction between the blade and endwall boundary layers. An existing three-dimensional Navier–Stokes flow solver with an explicit Runge–Kutta algorithm and a low-Reynolds-number k–ε turbulence model has been modified in order to simulate turbomachinery flows in a more efficient manner. The solver has been made to converge more rapidly through use of the multigrid technique.

    aiaa fan-inlet flow-field coupling. hunes, aiaa research on three dimensional compression scramjet inlet. yabin, x. / lian-jie, y. / peng, aiaa experimental investigation of flow and mixing in a gas turbine combustor model. findeisen. The generic, three-dimensional sidewall-compression inlets used in the present report haev been under study for several ears.y A review of the development of scramjet research at Langley Research Center is presented in reference 11; much of the inlet work de-otedv to that e ort was reported in references 12{


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Mach 10 experimental database of a three-dimensional scramjet inlet flow field by Scott D. Holland Download PDF EPUB FB2

Mach 10 Tunnel. The complete study was designed to demonstrate the utility of computational fluid dynamics as a design tool in hypersonic inlet flow fields, to provide a detailed account of the nature and structure of the inter-nal flow interactions, and to provide a comprehensive surface property and flow field database to determine theCited by: 6.

Get this from a library. Mach 10 experimental database of a three-dimensional scramjet inlet flow field. [Scott D Holland; Langley Research Center.]. obtained from the Mach 10 wind tunnel flow conditions.

Expanding the flow to Mach 10 at a free-stream unit Reynolds number of x per foot yielded a very low free-stream static pressure ( psia). The free-stream static temperature was 50 K. The inlet flow field was computed based on the assumption of laminar flow.

Computational Grid. CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): this document is intended primarily as a data release, the reader is directed to the primary document (ref. 2) for the overview and discussion of the entire program with comparative computational and experimental results.

Extensive study has been devoted to the threedimensional sidewall-compression scramjet inlet for. CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): The present work documents the computational results for a combined computational and experimental parametric study of the internal aerodynamics of a generic three-dimensional sidewall-compression scramjet inlet configuration at Mach The complete study was designed to demonstrate the utility of.

The present work documents the computational results for a combined computational and experimental parametric study of the internal aerodynamics of a generic three-dimensional sidewall-compression scramjet inlet configuration at Mach The three-dimensional Navier-Stokes code SCRAMIN was chosen for the computational portion of the study because it uses a well-known and well-proven.

Mach 10 experimental database of a three-dimensional scramjet inlet flow field [microform] / Scott D. Ho Computational parametric study of sidewall-compression scramjet inlet performance at mach 10 [microform] Experimental investigation of generic three-dimensional sidewall-compression scramjet inlets at Mach 6 i Mach 5 to 7 RBCC.

The tests were conducted at a condition replicating flight at Mach and a dynamic pressure of 48 kPa. The internal flowpath featured a rectangular-to-elliptical shape transition inlet designed for flight at M an elliptical combustor with a constant area and diverging section, and a three-dimensional thrust nozzle.

Inlet-injection was motivated by the possibility for skin-friction reduction in the combustion chamber of a flight style, three-dimensional, scramjet engine.

High Mach number flight, where skin. An illustration of an open book. Books. An illustration of two cells of a film strip. Video An illustration of an audio speaker. Full text of "A Computational and Experimental Investigation of a Three-Dimensional Hypersonic Scramjet Inlet Flow Field".

Wang (4), Mahapatra (5) and Liang (6) studied the numerical simulation of hypersonic inlet, and Haberle (7, 8) investigated scramjet inlet at Mach number 7. Chang (9,10) investigated hypersonic. A new methodology has been developed for the design of hypersonic scramjet inlets using gas dynamic relations.

The approach aims to find the optimal inlet geometry which has maximum total pressure recovery at a prescribed design free stream Mach number. The design criteria for inlet is chosen as shock-on-lip condition which ensures maximum capture area and minimum intake length.

generic three-dimensional sidewall-compression scram-jet inlet configuration at Mach The complete study was designed to demonstrate the utility of computational fluid dynamics (CFD) as a design tool in hypersonic inlet flow fields, to provide a detailed account of the nature and structure of the internal flow interactions, and to pro.

However, to test scramjet nozzles designed with non-uniform flow, a set of equipment that can mimic the target Mach number profile at the nozzle entrance is required in this research. As illustrated in Fig. 11, the non-uniform flow simulator consists of a 2D Laval nozzle, a boundary layer modification section, and an expansion section.

Get this from a library. Mach 10 computational study of a three-dimensional scramjet inlet flow field. [Scott D Holland; Langley Research Center.]. For a scramjet, the kinetic energy of the free stream air entering the scramjet engine is large compared to the energy released by the reaction of the oxygen content of the air with a fuel hydrogen.

Thus the heat released from combustion at Mach 25 is around 10% of the total enthalpy of the working fluid. This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. The Mach 10 Component of NASA’s Hyper-X Ground Test Program R.J.

Bakos* and C.-Y. Tsai† GASL, Ronkonkoma, NY and R.C. Ro 0 downloads 0 Views KB Size a generic three-dimensional sidewall compression scramjet inlet con guration at Mach 10 has been per-formed. The study was designed to demonstrate the utility of computational uid dynamics (CFD) as a design tool in hypersonic inlet ow elds, to examine the nature and structure of the ow interactions in-side an inlet subject to a high Mach number.

The three dimensional Reynolds-averaged Navier-Stokes equations and the Spalart-Allmaras turbulent model are adopted to simulate numerically the flow field of the three dimensional flow-path of a ram-rotor with different inlet relative Mach numbers (Ma0 = ~) and two kinds of throat length-height ratio.

It has been found that the flow fields are different with the changing of. The Mach 2 flow over a rearward-facing step has been investigated experimentally using these techniques.

The flow field contains many complex flow features including boundary layer separation, reattachment, viscous shear layer and expansion fan/shock wave interaction. Earlier investigations yielded a relatively sparse number of measurements.Experimental Study of Flow Unsteadiness in a Mach 9 Compression Ramp Interaction Using a Laser Schlieren System.

Experimental Study of Flow Unsteadiness in a Mach 9 Compression Ramp Interaction Using a Laser Schlieren System”, Measurement Science and Technology Journal, Vol. 14, No.7,pp. In the hypersonic regime the scramjet engine's specific thrust exceeds that of other propulsion systems.

This book, written by a leading researcher, describes the processes and characteristics of the scramjet engine in a unified manner, reviewing both the theoretical and experimental research.