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4 edition of Shock tunnel studies of scramjet phenomena 1993 found in the catalog.

Shock tunnel studies of scramjet phenomena 1993

Shock tunnel studies of scramjet phenomena 1993

supplement 10

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  • 22 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English


Edition Notes

StatementR.J. Stalker ... [et al.].
SeriesNASA contractor report -- 195038., NASA contractor report -- NASA CR-195038.
ContributionsStalker, R. J., Langley Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17012554M
OCLC/WorldCa33153669

Numerical study on the start and unstart phenomena in a scramjet inlet-isolator model 7 November | PLOS ONE, Vol. 14, No. 11 Performance comparison between waverider and wide-speed-range gliding vehicle based on CFD approachesCited by: Experimental study on the flow field behind a backward-facing step using a detonation-driven shock tunnel 28 December | Shock Waves, Vol. 15, No. 1 A Study on Increase of Duration of a Free Piston Shock TunnelCited by:

A free-piston shock tunnel (FPST) is one of the most useful ground testing facilities for hypervelocity flow research of re-entry vehicles and scramjet engines. For an efficient operation with tuned piston motion, the design of facility and the comprehension of the physical phenomena in a FPST, a numerical simulation which can properly predicts Cited by: Experiments on supersonic combustion ramjet propulsion in a shock tunnel - Volume - A. Paull, R. J. Stalker, D. J. Mee Skip to main content We use cookies to distinguish you from other users and to provide you with a better experience on our by:

The T4 shock tunnel at The University of Queensland is regularly used to perform supersonic combustion experiments. The fuel for the test model is supplied using a . The behavior of a ram-scram transition was examined using a direct-connect model scramjet experiment along with pressure measurements and high-speed laser interferometry. The work quantifies the sudden change in the wall static pressure profile and flame position that occurs as the downstream boundary condition abruptly changes when the flow becomes by:


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Shock tunnel studies of scramjet phenomena 1993 Download PDF EPUB FB2

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.

Get this from a library. Shock tunnel studies Shock tunnel studies of scramjet phenomena 1993 book scramjet phenomena supplement [R J Stalker; Langley Research Center.;]. 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 study, an ideal premixed flow is simulated by using the "frozen" free stream in the test section of a shock tunnel with nitrogen test gas. Shock Tunnel Studies of Scramjet Phenomena Pub Date: January Bibcode: .S Keywords: Fuel Combustion; Fuel Injection; Hydrogen Fuels; Shock Tests; Shock Tunnels; Shock Waves; Supersonic Combustion Ramjet Engines; Combustion Chambers; Hypersonic Flight; Hypervelocity; Author: R.

Stalker, R. Bakos, R. Morgan, L. Porter, D. Mee, A. Paull, S. Tuttle, J. Simmons, M. Shock tunnel studies of scramjet phenomena, supplement 7: Authors: Bakos, R. J.; These reports document the tests conducted in the reflected shock tunnel T4 and supporting research facilities that have been used to study the injection, mixing, and combustion of hydrogen fuel in generic scramjets at flow conditions typical of hypersonic.

Reports by the staff of the University of Oueensland on various research studies related to the advancement of scramjet technology are presented. These reports document the tests conducted in the reflected shock tunnel T4 and supporting research facilities that have been used to study the injection, mixing, and combustion of hydrogen fuel in generic scramjets at.

Reports by the staff of the University of Queensland on various research studies related to the advancement of scramjet technology are presented.

These reports document the tests conducted in the reflected shock tunnel T4 and supporting research facilities that have been used to study the injection, mixing, and combustion of hydrogen fuel in generic scramjets at Author: M.

Wendt, M. Nettleton, R. Morgan, K. Skinner, R. Casey, R. Stalker, C. Brescianini, A. Paull, G. A series of reports are presented on SCRAMjet studies, shock tunnel studies, and expansion tube studies. The SCRAMjet studies include: (1) Investigation of a Supersonic Combustion Layer; (2) Wall.

Duringthe free piston shock tunnel T4 was brought into operation, and a preliminary calibration was performed. This involved selection of a particular driver gas volumetric compression ratio (k - 60), and measurement of shock speeds and pressure history at the downstream end of the shock tube after shock Size: 5MB.

Abstract. An experimental study is conducted to investigate the phenomena of supersonic combustion by means of shock tunnel. By using shock tunnel, test air is compressed by reflected shock wave up to stagnation temperature of K and stagnation pressure of by: 1.

Shock tunnel studies of scramjet phenomena, supplement 5 A series of reports are presented on SCRAMjet studies, shock tunnel studies, and expansion tube studies. March Maureen. and the supersonic flow behind that shock is subjected to a simple wave unsteady expansion which produces the test flow. It is known that the finite mass of the secondary diaphragm must cause the flow to be different to this, and a more sophisticated model treats the diaphragm as a piston, which is set in motion by the arrival of the primary shock.

Shock tunnel experiments have been conducted within The University of Queensland's T4 Stalker Tunnel with a small airframe-integrated three-dimensional scramjet engine.

COVID Resources. Reliable information about the coronavirus (COVID) is available from the World Health Organization (current situation, international travel).Numerous and frequently-updated resource results are available from this ’s WebJunction has pulled together information and resources to assist library staff as they consider how to handle.

Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor. Part I: Shock-tunnel experiments. Combustion and Flame, Vol.Issue. 4, p. Krek, R. & Jacobs, P. STN, shock tube and nozzle calculations for A.

Exploratory study of transient unstart phenomena in a. Reports by the staff of the University of Queensland on various research studies related to the advancement of scramjet technology are presented. These reports document the tests conducted in the reflected shock tunnel T4 and supporting research facilities that have been used to study the injection, mixing, and combustion of hydrogen fuel in.

Unsteady pressure behavior in a ramjet/scramjet inlet. Control of Unstart Phenomenon in Scramjet Engines. Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor.

Part I: Shock-tunnel experiments. Combustion and Flame, Vol. No. by: Reports by the staff of the University of Oueensland on various research studies related to the advancement of scramjet technology are presented.

These reports document the tests conducted in the reflected shock tunnel T4 and supporting research facilities that have been used to study the injection, mixing, and combustion of hydrogen fuel in. Abstract. The interaction of a Shockwave with another Shockwave is an unavoidable phenomenon in high speed flows.

These interactions may lead to high pressure and thermal loads on the surface in the vicinity, deteriorates the aerodynamic performance of the system if present internally, and may also lead to the un-start of Scramjet engine due to Author: Abhishek Khatta, Gopalan Jagadeesh.

A stress-wave force balance for measurement of thrust, lift, and pitching moment on a large scramjet model (40 kg in mass, in in length) in a reflected shock tunnel. Brescianini C, Morgan RG () An ilnvestigation of a wall-injected Scramjet using a shock tunnel.

AIAA Paper 92– Google Scholar Dunn MG, Lordi JA, Wittliff CE, Holden MS () Facility requirements for hypersonic propulsion system : G. Smeets.SHOCK TUNNEL STUDIES OF SCRAM JET PHENOMENA FINAL TECHNICAL REPORT - NAGW - C_ / C/ Initially, work done under the grant was directed towards obtaining data at high enthaipies which could point to effects which may have a bearing on the NASP program.

The unstart phenomena in a model scramjet with a free stream Mach number of were investigated at an arc-heated hypersonic wind tunnel. High-speed schlieren imaging and high resonance frequency pressure measurements were used to capture the flow features during the unstart by: