Published 1995 by University of Queensland, National Aeronautics and Space Administration, National Technical Information Service, distributor in [Brisbane, Australia], [Washington, D.C, Springfield, Va .
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|Series||[NASA contractor report] -- NASA CR-199445., NASA contractor report -- NASA CR-199445.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Download Shock tunnel studies of scramjet phenomena 1994.
SHOCK TUNNEL STUDIES OF SCRAMJET PHENOMENA NASA GRANT NAGW - SUPPLEMENT I 0 In accord with the format of previous reports, this consists of a series of reports on specific projects. There is a brief introduction commenting on each report, and the project reports follow in the order of the headings in the introduction.
Shock Induced Heat Release - An Optical Study N. Ward This can be seen as an idealised study of scramjet operation with shock induced combustion following fuel-air-mixing in the intake. In this Shock tunnel studies of scramjet phenomena 1994. book, an ideal premixed flow is simulated by using the "frozen" free stream in the test section of a shock tunnel with nitrogen test gas.
Get this from a library. Shock tunnel studies of scramjet phenomena Supplements 11 and [United States. National Aeronautics and Space Administration.;]. Get this from a library. Shock tunnel studies of scramjet phenomena supplements 11 and [R G Morgan; R J Stalker; Alvord Paull; Langley Research Center.].
T5 Hypervelocity Shock Tunnel Facility. It is a free piston shock tunnel located at California Institute of Technology, USA. It is the largest free-piston shock tunnel in the world at a university. It is an impulse facility capable of reaching very high stagnation enthalpies (25 MJ/kg) and pressures (40 MPa).
The test time is on the order of 1 ms. A high enthalpy shock tunnel is a potential facility for gaining knowledge to develop modern aerothermodynamic and propulsion technologies.
The largest high enthalpy shock tunnel HIEST was built at NAL Kakuda inaiming for aerothermodynamic tests of Japan's space vehicle HOPE and scramjet propulsion systems. Selected topics from the Cited by: T4 - Free-piston driven shock tunnel The T4 Stalker Tube began operation in April and commenced routine operation, after a commissioning period, in September th shot of T4 was fired in August Experiments on supersonic combustion ramjet propulsion in a shock tunnel - Volume - A.
Paull, R. Stalker, D. MeeCited by: Scramjet programs refers to research and testing programs for the development of supersonic combustion ramjets, known as list provides a short overview of national and international collaborations, and civilian and military programs. The USA, Russia, India, and China (), have succeeded at developing scramjet technologies.
In the present work, an approach very similar to that proposed by Pecnik et al. is followed. Flamelets are solved and tabulated at a single reference pressure of p tab = bar, and at fixed temperatures at the fuel and oxidizer boundaries (T tab, Z = 1 = K and T tab, Z = 0 = K, respectively).
These conditions are representative of the conditions in the HyShot II by: Three-dimensional computational simulations of reactive flowfields within a hydrogen-fueled scramjet-like geometry experimentally tested in a free piston shock tunnel are presented.
The experimental configuration (Odam and Paull, AIAA Paper ) involves injection of hydrogen fuel into the scramjet inlet, followed by mixing, shock-induced Cited by: Hypersonic research in the shock tunnel Unknown Binding – January 1, by Charles E Wittliff Shock tunnel studies of scramjet phenomena 1994.
book See all formats and editions Hide other formats and editions. Price New from Used from Unknown Binding, "Please retry" Author: Charles E Wittliff. Shock tubes and shock tunnel are used to simulate re-entry, but the duration of a shock tunnel test is extremely short.
In order to apply TSP to high. Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor.
Part I: Shock-tunnel experiments Article in Combustion and Flame (4) January. Reservoir of and Pressure Studies in the a Reflected-Shock Hypersonic Tunnel By K. LAPWORTH and J. TOWNSEND Reports and Memoranda No.
* December, Summary. Temperatures and pressures have been measured in the shock-heated gas upstream of the nozzle of a reflected-shock hypersonic Size: 3MB. Stable isolator shock trains have been observed in dual-mode configurations by a number of experimental researchers. Typically, these observations are made indirectly through the measured pressure rise ahead of the injection location, e.g., ; but direct visualization of the shock train with schlieren and interferometry, notably during mode transition, has also been Cited by: Real gas effects dominate the hypersonic flow fields encountered by modern day hypersonic space vehicles.
Measurement of aerodynamic data for the design applications of such aerospace vehicles calls for special kinds of wind tunnels capable of faithfully simulating real gas effects.
A shock tunnel is an established facility commonly used along with special Cited by: 7. Hannemann, Klaus und Martinez Schramm, Jan und Karl, Sebastian und Laurence, Stuart () Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel.
20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, - JulyGlasgow, Scotland, United Kingdom. DOI: / Dieses Archiv kann nicht den Cited by: 5. oxygen and water vapor at the NASA Ames meter (16 inch) shock tunnel which they will use for scramjet performance tests.
The measurement technique is based on the use of diode lasers with superior wavelength and modal properties. These. Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow (SuDoc NAS ) [Holden, Michael S.] on *FREE* shipping on qualifying offers. Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow (SuDoc NAS )Author: Michael S.
Holden. The Hy-V Scramjet Flight Experiment is a research project being led by the University of Virginia, the goal of which is to better understand dual-mode scramjet combustion by analyzing and comparing wind tunnel and flight data.
The work is being conducted with industrial, academic and government collaborators. By using results obtained in tests on supersonic combustion of hydrogen in air, the conditions governing model size and operating pressure levels for shock tunnel experiments on models of flight vehicles with scramjet propulsion are established.
It is seen that large models are required. The development of the stress wave force balance is then described, and its use as Cited by: This paper reviews some basic research areas associated with Scramjet-powered hypersonic flying vehicle, particularly the forebody boundary-layer transition and intake shock-wave boundary-layer interactions (SBLI).
Some technical and physical challenges in aerodynamics, aero-thermodynamics, aero-design are visited with focuses being placed on hypersonic Author: Yu Feng Yao.
The elementary theory~ of the reflected-shock tunnel is outlined below, with particular reference to the interaction of the reflected shock with the contact surface. The results of experiments are included for comparison. To reduce viscous effects on the motion of the primary shock it is necessary to keep the ratio of the length File Size: 2MB.
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Understanding the causes and effects of explosions is important to experts in a broad range of disciplines, including the military, industrial and environmental research, aeronautic engineering, and applied mathematics.
Offering an introductory review of historic research, Shock Waves and Explosions brings analytic and computational methods to a wide audience in a clear and.
14 For comparison purposes, the scramjet engine design is compared side-by-side with the United States Air Force FC propulsion unit – the Pratt & Whitney F Turbofan, which has an unclassified maximum thrust (in the late models) of kN (29, lbf) .
A ratio of scramjet thrust to PW F thrust is provided as output. The high-pressure, high-temperature gas at the end of the shock tube acted as a reservoir for a Mach 4 contoured nozzle.
The shock tunnel was a pulsed facility, and test time was restricted by the shock tube volume and the mass flow rate through the nozzle. The total enthalpy conditions used in these experiments were, and MJ/: Eunju Jeong, Sean O’Byrne, In-Seuck Jeung, A. Houwing. Shock tunnel and numerical studies of a large inlet-fuelled inward turning axisymmetric scramjet.
CFD Analysis of Unsteady Combustion Phenomena in the HyShot-II Scramjet Configuration. Sebastian Karl, Stuart Laurence, On the Numerical Simulation of a Scramjet Intake using a Space-Time-Expansion Discontinuous Galerkin Scheme.
The value of the shock tube would be generally agreed, but the authors feel that the shock tunnel, also, has a useful place in hypersonic research. To illustrate this view, the present paper discusses recent work at the N.P.L. on the development of shock tunnels and associated instrumentation, andFile Size: 7MB.
Scramjet Engine is making headlines these days. The successful testing of Scramjet engine designed by ISRO represents a major milestone in India’s future space programs. But what is a Scramjet Engine. What is a Scramjet Engine.
To make it simple, a scramjet is a supersonic combusting ramjet). This is a variant of a ramjet jet engine in which combustion takes place in. The University of Queensland's institutional repository, UQ eSpace, aims to create global visibility and accessibility of UQ’s scholarly : Andrew Noel Ridings.
Scramjet programme is a fast developing field in the present world. There are many applications with scramjet. It provides a cheaper and efficient access to space. Scramjet has the potential for supersonic or hypersonic transportation.
Scramjet technologies are also used for military applications. But scramjet technologies still need developments. The flow field in a hypersonic inlet model at a design point of M = 6 has been studied experimentally.
The focus of the current study is to present the time-resolved flow characteristics of separation shock around the cowl and the correlation between the separation shock oscillation induced by the unstart flow and the wall pressure fluctuation when the inlet is in a state of : Chengpeng Wang, Xin Yang, Longsheng Xue, Konstantinos Kontis, Yun Jiao.
The Internet Archive offers o, freely downloadable books and texts. There is also a collection of million modern eBooks that may be borrowed by anyone with a free account. Borrow a Book Books on Internet Archive are offered in.
Numerical Simulation of a Ludwieg -tube Fuel Delivery System for Scramjet Experiments in Shock Tunnels Dhananjay Y.
Gangurde 1, David J. Mee 2 and Peter A. Jacobs 2 from four shots in the T4 Shock Tunnel that involved combustion tests of a scramjet model. • —It was reported in the open literature for the first time in the world that a scramjet had achieved more thrust than drag — the essence of flight — in the T4 facility at UQ.
Dr Allan Paull, Professor Stalker, and Dr David Mee “flew” a complete scramjet prototype in the T4 shock facility. A scramjet (supersonic combusting ramjet) is a variant of a ramjet airbreathing jet engine in which combustion takes place in supersonic airflow. As in ramjets, a scramjet relies on high vehicle speed to forcefully compress the incoming air before combustion (hence ramjet), but a ramjet decelerates the air to subsonic velocities before combustion, while airflow in a scramjet is.
Air-breathing hypersonic flight has long been recognized for its potential to enable both advanced military missions and (possibly) efficient access to space. It offers two principal advantages: high speeds, with associated reduction in time to target, and the potential for substantial performance.
The authors acknowledge BrahMos Aerospace Private Limited, New Delhi, and the IISc Startup Grant for funding this research work. The authors would also like to thank Shivashankar and Shantha Kumar for their help in operating the m hypersonic wind tunnel, Murthy and Raju for their help in fabrication, Parthiban (Novatek Automation) for designing the mechanism of the Author: Manoj Kumar K.
Devaraj, Prahallada Jutur, Srisha M. Rao, Gopalan Jagadeesh, Ganesh T. Anavardh. Lu FK. Book review of Shock Wave Dynamics: Derivatives and Related Topics, Shock Waves, 23(6), Maddalena L, Vergine F, Crisanti M.
Vortex dynamics studies in supersonic flow: Merging of co-rotating streamwise vortices, Physics of Fluids, 26, Experimental visualizations by Laurence et al.
(, ) of unstart in a model HyShot-2 scramjet tested at DLR's high-enthalpy shock tunnel have recently shown that, in real configurations, the description is much more complicated because the compression wave produced by thermal choking propagates upstream across a turbulent flow where Cited by: A scramjet (supersonic combustion ramjet) is a variation of a ramjet distinguished by supersonic combustion.
At higher speeds, it is necessary to combust supersonically to maximize the efficiency of the combustion process. Projections for the top speed of a scramjet engine (without additional oxidiser input) vary between Mach 12 and Mach 24 (orbital velocity).