NDLI: Theoretical analysis of effects of boundary layer bleed on scramjet thrust

Content Provider	Springer Nature Link
Author	Yue, LianJie Xu, XianKun Chang, XinYu
Copyright Year	2013
Abstract	The effects of boundary layer bleed on the scramjet thrust are studied in the present paper. A theoretical model is developed to evaluate the thrust increment and influencing factors. The thrust increment resulting from the bleed is dominated by the rise in total pressure recovery and bleed mass flow rate. The bleed mass flow rate exerts stronger impact on the engine thrust than the total pressure. According to current bleed design, it is a severe challenge for the engine to enhance its total pressure to maintain the original thrust when there is no bleeding. Furthermore, the initial total pressure recovery, fuel mass addition, combustion efficiency and area ratio of engine exit to entrance can affect the contributions of the bleeding to the thrust increment. The scramjet needs a higher rise in total pressure recovery to counteract the negative effect of bleed mass loss at higher initial total pressure recovery or larger area ratio of engine exit/entrance. More heat release results in a little lower demand on the rise in total pressure recovery for maintaining the scramjet thrust. These results will aid in understanding the fundamental mechanism of bleeding on engine thrust.
Starting Page	1952
Ending Page	1961
Page Count	10
File Format	PDF
ISSN	16747348
Journal	Science in China Series G
Volume Number	56
Issue Number	10
e-ISSN	18691927
Language	English
Publisher	Springer Berlin Heidelberg
Publisher Date	2013-09-21
Publisher Place	Berlin, Heidelberg
Access Restriction	One Nation One Subscription (ONOS)
Subject Keyword	scramjet boundary layer bleed theoretical analysis engine thrust Physics Classical Continuum Physics Astronomy, Observations and Techniques
Content Type	Text
Resource Type	Article
Subject	Physics and Astronomy

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

Aerothermal characteristics of bleed slot in hypersonic flows

Theoretical modeling of chemical nonequilibrium stagnation point boundary layer heat transfer under rarefied conditions

DNS of a spatially evolving hypersonic turbulent boundary layer at Mach 8

Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions

Recent advances in active control of turbulent boundary layers

Interaction between strain and vorticity in compressible turbulent boundary layer

Series solution of non-similarity natural convection boundary-layer flows over permeable vertical surface

Experimental study of a supersonic turbulent boundary layer using PIV

Transition prediction of the supersonic boundary layer on a cone under the consideration of receptivity to slow acoustic waves

Theoretical analysis of effects of boundary layer bleed on scramjet thrust

Similar Documents

Aerothermal characteristics of bleed slot in hypersonic flows

Theoretical modeling of chemical nonequilibrium stagnation point boundary layer heat transfer under rarefied conditions

DNS of a spatially evolving hypersonic turbulent boundary layer at Mach 8

Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions

Recent advances in active control of turbulent boundary layers

Interaction between strain and vorticity in compressible turbulent boundary layer

Series solution of non-similarity natural convection boundary-layer flows over permeable vertical surface

Experimental study of a supersonic turbulent boundary layer using PIV

Transition prediction of the supersonic boundary layer on a cone under the consideration of receptivity to slow acoustic waves

Theoretical analysis of effects of boundary layer bleed on scramjet thrust