NDLI: Three-Dimensional Supersonic Minimum Length Nozzle Design at High Temperature for Arbitrary Exit Cross Section

Content Provider	Springer Nature Link
Author	Abada, Omar Zebbiche, Toufik Abdallah El Hirtsi, Ahmed
Copyright Year	2014
Abstract	The scope of this work was to perform a new three-dimensional MLN shape design of supersonic nozzles with an arbitrary exit cross section. The shape design is done by making a transition from the axisymmetrical nozzle using the streamline definition in space. The study is made at high temperature, however, less than the dissociation temperature. Studying asymmetric nozzles is very important for the improvement in the axisymmetric nozzles efficiency, higher Mach number, mass and thrust coefficient. Three cases are considered in order to find a three-dimensional nozzle shape with equal mass, the same exit Mach number and the same throat area compared with the axisymmetric geometry. The difference between the perfect gas model and our high-temperature model is presented. Calculation can be performed for any selected 3D nozzle exit cross section. Hence, an infinite number of nozzle shapes are available, depending on the selected exit Mach number, stagnation temperature or exit cross-sectional shape. The application is for air.
Starting Page	8233
Ending Page	8245
Page Count	13
File Format	PDF
ISSN	13198025
Journal	Arabian Journal for Science and Engineering
Volume Number	39
Issue Number	11
e-ISSN	21914281
Language	English
Publisher	Springer Berlin Heidelberg
Publisher Date	2014-10-10
Publisher Place	Berlin, Heidelberg
Access Restriction	One Nation One Subscription (ONOS)
Subject Keyword	Nozzle shape Supersonic flow High-temperature flow Axisymmetric MLN nozzle Method of characteristics Mach number Engineering Science
Content Type	Text
Resource Type	Article

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

Three-Dimensional Supersonic Minimum Length Nozzle Design at High Temperature for Arbitrary Exit Cross Section

Rapid design method and new contours for a class of three dimensional supersonic nozzle of arbitrary exit cross section

Supersonic two-dimensional minimum length nozzle design at high temperature (2005).

A novel contour design technique of super/hypersonic nozzle diverging section with sharing throat

Supersonic minimum length nozzle design for dense gases

Active control of supersonic jets operating in various flow regimes.

Three-dimensional supersonic nozzles and inlets of arbitrary exit cross section

Design of a continuously variable Mach-number nozzle

Effect of stagnation temperature on the supersonic axisymmetric minimum length nozzle conception with application for air

Three-Dimensional Supersonic Minimum Length Nozzle Design at High Temperature for Arbitrary Exit Cross Section

Similar Documents

Three-Dimensional Supersonic Minimum Length Nozzle Design at High Temperature for Arbitrary Exit Cross Section

Rapid design method and new contours for a class of three dimensional supersonic nozzle of arbitrary exit cross section

Supersonic two-dimensional minimum length nozzle design at high temperature (2005).

A novel contour design technique of super/hypersonic nozzle diverging section with sharing throat

Supersonic minimum length nozzle design for dense gases

Active control of supersonic jets operating in various flow regimes.

Three-dimensional supersonic nozzles and inlets of arbitrary exit cross section

Design of a continuously variable Mach-number nozzle

Effect of stagnation temperature on the supersonic axisymmetric minimum length nozzle conception with application for air

Three-Dimensional Supersonic Minimum Length Nozzle Design at High Temperature for Arbitrary Exit Cross Section