2 edition of Simulation of a hydrocarbon fueled scramjet exhaust found in the catalog.
Simulation of a hydrocarbon fueled scramjet exhaust
by National Aeronautical and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
Written in English
|Statement||Jarvis Leng ; prepared for Langley Research Center under contract NAS1-16401|
|Series||NASA contractor report -- 3583|
|Contributions||Langley Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Grumman Aerospace Corporation|
|The Physical Object|
|Pagination||vii, 24 p. :|
|Number of Pages||24|
problem of scramjet fuel injection is that the airflow is quite fast, meaning that there is minimal time for the fuel to mix with the air and ignite to produce thrust (essentially milliseconds).Hydrogen is the main fuel used for combustion. Hydrocarbons present more of a challenge. History Cyrano de Bergerac. L'Autre Monde: ou les États et Empires de la Lune (Comical History of the States and Empires of the Moon) () was the first of three satirical novels written by Cyrano de Bergerac, that are considered among the first science fiction C Clarke credited this book with inventing the ramjet, and being the first example of a rocket-powered space flight.
Experimental and Numerical Investigation of a Solid-Fuel Rocket Scramjet Combustor. Journal of Propulsion and Power, Vol. 32, Issue. 2, p. Email your librarian or administrator to recommend adding this book to your organisation's collection. The Scramjet Engine. “Design analysis of the model hydrocarbon fueled engine performance. "This is the first time we have flight tested a hydrocarbon-fueled scramjet accelerating from Mach 6 to Mach 8," said NASA Hypersonics Project Scientist Ken Rock, based at NASA'S Langley Research Center in Hampton, Va. "At Mach 6 the inlet compression and combustion process was designed to reduce the flow to below Mach 1 -- subsonic combustion.
"This is the first time we have flight tested a hydrocarbon-fueled scramjet accelerating from Mach 6 to Mach 8," said NASA Hypersonics Project Scientist Ken Rock, based at NASA'S Langley Research. Fuel droplets were observed to be trapped on the exhaust side of the topland crevice even after exhaust valve opening (EVO). The overall trends predicted in the simulation study are similar to those observed in an experimental study conducted elsewhere, though quantitative agreement is less satisfactory.
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Simulation of a hydrocarbon fueled scramjet exhaust. Washington, D.C.: National Aeronautical and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.: For sale by the National Technical Information Service], (OCoLC) Material Type: Government publication, National government publication: Document.
Exhaust nozzle flow fields for a fully integrated, hydrocarbon burning scramjet were calculated for flight conditions of M (undisturbed free stream) = 4 at Simulation of a hydrocarbon fueled scramjet exhaust.
Washington, D.C.: [Springfield, Va: National Aeronautical and Space Administration, Scientific and Technical Information Branch ; For sale by the National Technical Information Service] MLA Citation. Leng. Simulation of a hydrocarbon fueled scramjet exhaust / By J. Leng, United States.
National Aeronautics and Space Administration. Scientific and Technical Information Branch., Grumman Aerospace Corporation. and Langley Research Center. Abstract Topics: Aircraft exhaust emissions. prototype. This report describes the definition of such exhaust simulation gases for a hydrocarbon fueled, fully-integrated scramjet vehicle.
The basis for substitute-gas simulation of scramjet exhausts is described in detail in Ref 3. A typical nozzle profile is chosen, and the actual scramjet exhaust flow is calculated using the method of.
Experimental Investigation of Hydrocarbon-fuel Ignition in Scramjet Combustor Chinese Journal of Aeronautics, Vol.
17, No. 2 Numerical analysis of supersonic combustion ramjet with upstream fuel. 1. Introduction. Hydrogen fueled dual-mode scramjet engines can operate on a wide range of flight Mach numbers and have considerable potential for trans-atmospheric vehicle applications.Hydrogen possesses superior characteristics to any other hydrocarbon fuel in terms of ignitability, low ignition delay, and higher flame stability.
Numerical and experimental study of fuel pre-injection in the inlet of a high-velocity air-breathing engine 21 October | Combustion, Explosion, and Shock Waves, Vol.
53, No. 5 Numerical Simulation about Mixing Characteristics of an Inlet-Fueled Scramjet Engine. In this paper, we present a methodology for the numerical simulation of the reacting flows of multicomponent fluid mixtures in a scramjet combustor based on solving the Navier-Stokes equation system.
The combustion dynamics depending on the oxidizer’s oxidation ratio is studied, and the methodology of the numerical simulation on the multiprocessor supercomputer K is. “Hydrocarbon-fueled scramjet combustor investigation,” AIAA Paper 90− Kopchenov, V.
and Lomkov, K. “The enhancement of the mixing and combustion processes applied to scramjet engines,” AIAA Paper 92– A kerosene-fueled scramjet combustor was numerically analyzed in order to meet the requirement of thrust for a hypersonic test vehicle.
The internal configuration of the fuel injection struts and fuel injection was arrived through computational fluid dynamics (CFD) study. The combustor was tested in the hypersonic test facility at DRDL.
Though it seems like H 2 is ideal fuel for high-speed air breathing engines; it possesses some disadvantages also. The density of H 2 ( kg/m 3) is very less as compared to other hydrocarbon fuel like JP-8 ( kg/m 3) at standard pressure and temperature [, ].It is for these reasons that todays’ aircraft still use hydrocarbon based fuels as compared to H 2.
Fuel Injection and Mixing in a Mach 8 Hydrocarbon-Fuelled Scramjet Z. Denman1, V. Wheatley1, M. Smart1 and A. Veeraragavan1 1Centre for Hypersonics The University of Queensland, QueenslandAustralia Abstract Three-dimensional, non-reacting, computational ﬂuid dynam-ics simulations of an elliptical scramjet combustor with cav.
capabilities for both fuel and overall engine design in lowering the starting Mach number; these results are presented here. The analysis has shown that a scramjet with a starting Mach number of is not currently possible with the fuels researched unless fuel additives or.
Waltrup PJ () Upper bounds on the flight speed of hydrocarbon-fueled scramjet-powered vehicles. J Propul Power 17(6)– CrossRef Google Scholar Wang P, Bai XS () Large eddy simulation of turbulent premixed flames using level-set G-equation.
To figure out the abnormal flow characteristics and thermal performance of supercritical fluids, some detailed information of supercritical pressure n-decane flowing in a horizont. Audio Books & Poetry Community Audio Computers, Technology and Science Music, Arts & Culture News & Public Affairs Non-English Audio Spirituality & Religion Librivox Free Audiobook Academy Pod Stars Applesauce Scandalous Beauty - A Makeup and Beauty Podcast by Erin Baynham Cubbie Correlation Elevate Christian Disability Trust Indian Raaga on.
HyTech is focused on expanding the technology base for liquid-hydrocarbon-fueled scramjet propulsion systems and is complementary in many ways to similar hydrogen-fueled hypersonic programs, such.
SIMULATION OF HYPERSONIC SCRAMJET EXHAUST By Ro A. Oman, K. M, Foreman, Jo Leng, and H. Hopkins Research Department Grumman Aerospace Corporation Bethpage, New York INTRODUCTION AND SUMMARY This report describes a plan and some preliminary analysis for the accurate simulation of pressure distributions on the.
Roux et al. [21,22] carried out thermodynamic analysis on ideal scramjets. Yang et al.  conducted thermodynamic analysis on specific thrust of hydrocarbon fueled scramjet and considered the. The leader in fuel-cooled hydrocarbon technology Aerojet Rocketdyne is uniquely positioned to offer a variety of liquid-fueled propulsion system concepts for hypersonic flight.
At the heart of these systems is a dual-mode scramjet, allowing the engine to function as a subsonic combustion ramjet at low supersonic speeds (Mach ) and as a supersonic combustion ramjet (scramjet) at high.A scramjet (supersonic combustion ramjet) is a variant of a ramjet airbreathing jet engine in which combustion takes place in supersonic in ramjets, a scramjet relies on high vehicle speed to compress the incoming air forcefully before combustion (hence ramjet), but whereas a ramjet decelerates the air to subsonic velocities before combustion, the airflow in a scramjet is supersonic.Using fuel for engine cooling is nothing new, but the cooling system will also act as a chemical reactor, breaking long-chain hydrocarbons down into short-chain hydrocarbons that burn more rapidly.
Hyper-X Mach XD: A version of the XA with a hydrogen-powered scramjet engine with a maximum speed of Mach Fastt.