NDLI: Experimental study on the flow field behind a backward-facing step using a detonation-driven shock tunnel

Please wait, while we are loading the content...

Experimental study on the flow field behind a backward-facing step using a detonation-driven shock tunnel

Content Provider	Springer Nature Link
Author	Kim, T. H. Yoshikawa, M. Obara, T. Ohyagi, S.
Copyright Year	2005
Abstract	The supersonic combustion RAM jet (SCRAM jet) engine is expected to be used in next-generation space planes and hypersonic airliners. To develop the engine, stabilized combustion in a supersonic flow field must be attained even though the residence time of flow is extremely short. A mixing process for breathed air and fuel injected into the supersonic flow field is therefore one of the most important design problems. Because the flow inside the SCRAM jet engine has high enthalpy, an experimental facility is required to produce the high-enthalpy flow field. In this study, a detonation-driven shock tunnel was built to produce a high-enthalpy flow, and a model SCRAM jet engine equipped with a backward-facing step was installed in the test section of the facility to visualize flow fields using a color schlieren technique and high-speed video camera. The fuel was injected perpendicularly to a Mach 3 flow behind the backward-facing step. The height of the step, the injection distance and injection pressure were varied to investigate the effects of the step on air/fuel mixing characteristics. The results show that the recirculation region increases as the fuel injection pressure increases. For injection behind the backward-facing step, mixing efficiency is much higher than with a flat plate. Also, the injection position has a significant influence on the size of the recirculation region generated behind the backward-facing step. The schlieren photograph and pressure histories measured on the bottom wall of the SCRAM jet engine model show that the fuel was ignited behind the step.
Starting Page	1
Ending Page	12
Page Count	12
File Format	PDF
ISSN	09381287
Journal	Shock Waves
Volume Number	15
Issue Number	1
e-ISSN	14322153
Language	English
Publisher	Springer-Verlag
Publisher Date	2005-12-28
Publisher Place	Berlin, Heidelberg
Access Restriction	One Nation One Subscription (ONOS)
Subject Keyword	SCRAM jet engine Detonation-driven shock tunnel Backward-facing step Supersonic combustion Condensed Matter Acoustics Thermodynamics Engineering Fluid Dynamics Fluids Engineering Thermodynamics, Transport Phenomena
Content Type	Text
Resource Type	Article
Subject	Physics and Astronomy Mechanical Engineering

Sl.	Authority	Responsibilities	Communication Details
1	Ministry of Education (GoI), Department of Higher Education	Sanctioning Authority	https://www.education.gov.in/ict-initiatives
2	Indian Institute of Technology Kharagpur	Host Institute of the Project: The host institute of the project is responsible for providing infrastructure support and hosting the project	https://www.iitkgp.ac.in
3	National Digital Library of India Office, Indian Institute of Technology Kharagpur	The administrative and infrastructural headquarters of the project	Dr. B. Sutradhar bsutra@ndl.gov.in
4	Project PI / Joint PI	Principal Investigator and Joint Principal Investigators of the project	Dr. B. Sutradhar bsutra@ndl.gov.in Prof. Saswat Chakrabarti will be added soon
5	Website/Portal (Helpdesk)	Queries regarding NDLI and its services	support@ndl.gov.in
6	Contents and Copyright Issues	Queries related to content curation and copyright issues	content@ndl.gov.in
7	National Digital Library of India Club (NDLI Club)	Queries related to NDLI Club formation, support, user awareness program, seminar/symposium, collaboration, social media, promotion, and outreach	clubsupport@ndl.gov.in
8	Digital Preservation Centre (DPC)	Assistance with digitizing and archiving copyright-free printed books	dpc@ndl.gov.in
9	IDR Setup or Support	Queries related to establishment and support of Institutional Digital Repository (IDR) and IDR workshops	idr@ndl.gov.in

Experimental study on the flow field behind a backward-facing step using a detonation-driven shock tunnel

Advances in detonation driving techniques for a shock tube/tunnel

Flow visualization of supersonic laminar flow over a backward-facing step via NPLS

Reinitiation process of detonation wave behind a slit-plate

Experimental Investigation of Nozzle Exit Reflector Effect on Supersonic Jet

The effect of injection angle on mixing and flame holding in supersonic combustor

Oxyhydrogen combustion and detonation driven shock tube

Detonation Initiation by Shock Reflection from an Orifice Plate

Methods for investigating supersonic ground effect in a blowdown wind tunnel

Experimental study on the flow field behind a backward-facing step using a detonation-driven shock tunnel

Similar Documents

Experimental study on the flow field behind a backward-facing step using a detonation-driven shock tunnel

Advances in detonation driving techniques for a shock tube/tunnel

Flow visualization of supersonic laminar flow over a backward-facing step via NPLS

Reinitiation process of detonation wave behind a slit-plate

Experimental Investigation of Nozzle Exit Reflector Effect on Supersonic Jet

The effect of injection angle on mixing and flame holding in supersonic combustor

Oxyhydrogen combustion and detonation driven shock tube

Detonation Initiation by Shock Reflection from an Orifice Plate

Methods for investigating supersonic ground effect in a blowdown wind tunnel

Experimental study on the flow field behind a backward-facing step using a detonation-driven shock tunnel