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Friday, April 17, 2020 | History

2 edition of Combustion of hydrogen injected into a supersonic airstream found in the catalog.

Combustion of hydrogen injected into a supersonic airstream

David F. Dyer

Combustion of hydrogen injected into a supersonic airstream

a guide to the Hiss computer program

by David F. Dyer

  • 5 Want to read
  • 36 Currently reading

Published by U.S. National Aeronautics and Space Administration, for sale by the National Technical Information Service in Washington, Springfield, Va .
Written in English

    Subjects:
  • Hydrogen -- Combustion.,
  • Combustion -- Research -- Computer programs.

  • Edition Notes

    StatementD. F. Dyer, G. Maples, and D. B. Spalding.
    SeriesNASA contractor report ; NASA CR-2655, NASA contractor report -- NASA CR-2655.
    ContributionsNaples, G., Spalding, D. B. 1923-, United States. National Aeronautics and Space Administration., Fluid Mechanics and Thermal Systems, Inc.
    The Physical Object
    Paginationiii, 74 p. :
    Number of Pages74
    ID Numbers
    Open LibraryOL17645424M

    One way to do it is to use fuel injectors that protrude, at an angle, into the supersonic airstream. They generate small shock waves that mix oxygen with fuel as soon as it is injected. @article{osti_, title = {Operating characteristics of a hydrogen-argon plasma torch for supersonic combustion applications}, author = {Barbi, E. and Mahan, J.R. and O'brien, W.F. and Wagner, T.C.}, abstractNote = {The residence time of the combustible mixture in the combustion chamber of a scramjet engine is much less than the time normally required for complete combustion.


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Combustion of hydrogen injected into a supersonic airstream by David F. Dyer Download PDF EPUB FB2

The mathematical and physical basis of the SHIP computer program which embodies a finite-difference, implicit numerical procedure for the computation of hydrogen injected into a supersonic airstream at an angle ranging from normal to parallel to the airstream main flow direction is by: Combustion of hydrogen injected into a supersonic airstream (the ship computer program).

Washington: National Aeronautics and Space Administration ; Springfield, Va.: For sale by the National Technical Information Service, Hydrogen burns when injected into a supersonic airstream at an angle ranging from normal to parallel to the airstream main flow brium combustion is.

Combustion of hydrogen injected into a supersonic airstream. Washington: U.S. National Aeronautics and Space Administration ; Springfield, Va.: For sale by the National Technical Information Service, A computer program based on a finite-difference, implicit numerical integration scheme is described for the prediction of hydrogen injected into a supersonic airstream at an angle ranging from normal to parallel to the airstream main flow direction.

Supersonic Combustion of Hydrogen in a Vitiated Airstream Using Transverse Injection. Akira Yoshida and Hiroshi TsujiCited by: Supersonic combustion of hydrogen injected perpendicular to a ductedvitiated airstream.

Combustion of kerosene in a supersonic airstream - Thermal efficiency of selected injection configurations. Owens and Supersonic Combustion of Hydrogen Fuel Injection Locations in a Cavity-Based by: 9. Experimental investigation of combustion of hydrogen injected parallel to supersonic airstream through strut has been investigated at the Institute of Chemical Propulsion, DLR [18], [19] using a laboratory supersonic combustor having one-sided divergent wall as Cited by: 5.

The aerothermodynamic processes in the supersonic combustion chamber are complex and closely related. The comparable time scales lead to a closely coupled turbulent mixing and chemical reaction by: 4.

Combustion of hydrogen injected into a supersonic airstream: a guide to the Hiss computer program /. A numerical study on mixing and combustion of hydrogen transversely injected into a main airstream is performed, by solving two-dimensional full Navier–Stokes equations.

The focus of this paper is to study the means of increasing the mixing and combustion efficiencies, and the flameholding capability for supersonic propulsion application by changing the main flow inlet Cited by: Supersonic combustion of hydrogen injected perpendicular to a ducted vitiated airstream.

The reaction of hydrogen injected into a supersonic vitiated airstream from perpendicular injectors equally spaced over opposite walls of a two-dimensional duct is experimentally investigated.

Information is obtained in the form of pitot pressure and Author: J. Eggers and R. Rogers. MCS 7 Chia Laguna, Cagliari, Sardinia, Italy, SeptemberNUMERICAL INVESTIGATION ON THE EFFECT OF INCIDENT SHOCK WAVE ON MIXING AND COMBUSTION OF TRANSVERSE HYDROGEN INJECTION IN SUPERSONIC AIRSTREAM Y.

Shoraka* and S. Tabejamaat* [email protected] * Aerospace Engineering Department. Hydrogen was injected into a vitiated Combustion of hydrogen injected into a supersonic airstream book airstream by means of pylon-like fuel injectors.

The supersonic flame was stabilized in a purely kinetical way; i.e., by means of fuel self-ignition. Audio Books & Poetry Community Audio Computers, Technology and Science Music, Arts & Culture News & Public Affairs Non-English Audio Spirituality & Religion.

Librivox Free Audiobook. StoryTime with BrainyToon: Podcast for Kids NFB Radio Sermon Podcast Backstage Opera for iPhone/iPod Pauping Off All Steak No Sizzle Podcast Church of the Oranges. Fuel Injection and Flameholding in High Speed Combustion Systems.

Molder, S., and Szpiro, E. J., “Secondary Liquid Injection into a Supersonic Airstream”,Journal of Spacecraft and “Effect of Different Methods of Injection of Hydrogen on Completeness of Its Combustion in a Supersonic Air Flow”, Soviet Journal of Applied Physics Cited by: 4.

The flame was initiated with hydrogen injection at the base of the step. After this base pilot ignited, the upstream, ramp, and downstream injection occurred according to the pre-defined test matrix. Upon completion of this series, ethylene was tested in a similar fashion.

Combustion of hydrogen injected into a supersonic airstream (the ship computer program) / (Washington: National Aeronautics and Space Administration ; Springfield, Va.: For sale by the National Technical Information Service, ), by N.

Markatos, D. Tatchell, D. Spalding, Fluid Mechanics and Thermal Systems, and United States. However, research activities have continued to examine fuel injection schemes to enhance fuel-air mixing and to study alternative or combined cycle propulsion systems.

The purpose of this paper is to provide a review of experimental supersonic combustion research efforts related to airbreathing propulsion systems at LaRC since The five propulsion facilities comprising the NASA Langley Scramjet Test Complex are listed in Table 1.

The complex consists of the Direct-Connect Supersonic Combustion Test Facility (DCSCTF), the Combustion-Heated Scramjet Test Facility (CHSTF), is injected into the airstream from instream injectors and premixed before hydrogen is injected File Size: KB.

An experimental study of supersonic combustion of gaseous hydrogen injected trans-versely into a vitiated airstream has been carried out. The ignition and performance characteristics of the hydrogen fuelled stepped combustor have been determined.

A numerical study on mixing of hydrogen injected into a supersonic air stream has been performed by solving two-dimensional full Navier-Stokes equations. An explicit Harten-Yee Non-MUSCL Modified-flux-type TVD scheme has been used to solve the system of equations, and a zero-equation algebraic turbulence model to calculate the eddy viscosity Cited by: 2.

USA USDA USA US A US A US A US D A USD A US DA US A US A US A Authority US United States Prior art keywords supersonic compressor fuel air engine Prior art date Legal status (The legal status is an assumption and is not a legal by: 9. Rogers, R. b A study of the mixing of hydrogen injected normal to a supersonic airstream.

NASA Tech. Rep. TN D Rothstein, A. A study of the normal injection of hydrogen into a heated supersonic Cited by: The code solves the three-dimensional Reynolds time-averaged complete Navier-Stokes equations including transport equations for a four species, two reaction, global finite rate chemistry model.

The code was applied to the case of transverse injection of hydrogen from a sonic circular orifice into a supersonic : K. Uenishi, G. Northam and R. Rogers. An investigation has been conducted to study the cold-flow mixing of hydrogen injected from multiple injectors oriented normal to a supersonic airstream.

The injec- tors were flush mounted on a flat plate and laterally spaced at and injector diameters. to free-stream dynamic pressure from to into a Mach airstream having a. NUMERICAL INVESTIGATION OF HYDROGEN AND KEROSENE COMBUSTION IN SUPERSONIC AIR STREAMS A.A.

Taha 1, S.N. Tiwari 2, and T.O. Mohieldin a College of Engineering and Technology Old Dominion University, Norfolk, VA ABSTRACT The effect of mixing schemes on the combusion of both gaseous hydrogen and liquid kerosene is.

Fuel injection is a system for injecting the fuel into combustor. To promote fuel and air mixing combustor of a scramjet engine, fuel is injected as a succession of pulses into the airstream through the combustor.

There are several key issues that must be considered in the design of an efficient fuel injector. Rogers, “ A study of the mixing of hydrogen injected normal to a supersonic airstream,” NACA Technical Report No.

TN D (). Google Scholar; A. Rothstein and P. Wantuck, “ A study of normal injection of hydrogen into a heated supersonic flow using planar laser-induced fluorescence,” AIAA Paper No. ().Cited by: Scramjet (supersonic combustion ramjet) engines offer tremendous potential for high-speed transport of missiles and aircraft.

High speed air is compressed by the ram effect in the inlet of the scramjet. Fuel (typically hydrogen or some hydrocarbon) is injected into the supersonic airstream and, hopefully, mixes, ignites, and burns. Hydrogen was injected transversely as staged, underexpanded jets behind a rearward facing step into a ducted Mach 2 air free stream.

The effects of the chemical reaction on the supersonic flowfield was investigated using shadowgraphs, broadband flame emission photography, and planar laser-induced fluorescence of OH. Hi friends I'm trying to model a supersonic reacting flow with crosswise injection of hydrogen gas at mach 1 into mach main air stream.

I'm using finite rate combustion model with the fluent solver I want to find the combustion efficieny. And in the papers its given as ηc = 1 – [ ∫αρu dA / ∑m fuel in ] ; α = mass fraction of fuel.

At still higher Mach numbers, such deceleration becomes more difficult and costly in terms of pressure losses, and it is necessary to make provision for the combustion chamber to burn its fuel in the supersonic airstream.

Such specialized ramjets are called scramjets (for supersonic combustion ramjets). Wall injection of solid H 2 particles into the supersonic airstream of a combustor has been investigated to determine if it can provide ultrafast distributed fuel mixing for a practical large scramjet engine [1].

Supersonic Combustion of Liquid Hydrogen using Slotted Shaped Pylon Injectors hydrogen combustion process, subsequently serve as reaction partners for the exothermic fuel oxidation reactions and are finally consumed by chain terminating reactions.

Therefore the detection of OH self-fluorescence is an appropriate means to. Chief Scientist Carl Nelson demonstrates how the combustion of hydrogen gas depends on the amount of oxygen present. A balloon filled with % hydrogen is ignited with a small flame.

As the flame. Supersonic combustion research In chapter 1, it was noted that the problem of designing a practical scramjet-powered vehicle remains unsolved, despite decades of research. The purpose of this chapter is to provide a brief background of this research effort in or-der to demonstrate how the research presented here fits into a much larger Size: KB.

injected into an air stream (Xuejun Fan and Sung ). This delay results from the time taken for the liquid hydrocarbon to first vaporise, then penetrate into the airstream and finally mix with the air to form the combustion fuel (Walker ). One approach to solving this problem would be to elongate the combustion chamber.

USA USA USA USA US A US A US A US A US A US A US A US A US A US A US A US A Authority US United States Prior art keywords airfoil fuel combustion supersonic airstream Prior art date Legal. BOOK C. Segal, “The Scramjet “Effects of Mixing Schemes on Kerosene Combustion in a Supersonic Airstream”, Journal of Propulsion and Power D.

F., Segal, C., Goldman, A. and Ortwerth, P. “Effects Of Hydrogen And Ethylene Injection Schemes In A Supersonic Airstream”, 12 th International Space Planes and Hypersonic. Then it acts as a scramjet for the higher velocities. This switch from ramjet to scramjet is possible by changing the position that the hydrogen is injected into the airflow.

By injecting the hydrogen into the airstream earlier during scramjet mode, the hydrogen still has enough time to mix and burn properly (Pope-2 47).Proof-of-Principle Experiment of a Shock-Induced Combustion Ramjet RTO-EN-AVT 8 - 3 injected from a test object into a supersonic air flow having a static temperature which is representative for typical hypersonic operational conditions.

Figure 2 displays the axi-symmetrical test object. After mixingAuthor: R.G. Veraar, A.E.H.J. Mayer, J. Verreault, R.A. Stowe, R. Farinaccio, P.G. Harris.The variable Prt⁄Sct turbulence model is used to simulate the SCHOLAR supersonic combustion experiments.

The experiments include one model with normal hydrogen injection into a vitiated airstream at Machwhile the other injects hydrogen at Mach and an angle of 30° to the vitiated by: 8.