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Inlet Design for Japhar Flight Test Vehicle

Duveau, Ph. and Esch, H. and Triesch, K. (2001) Inlet Design for Japhar Flight Test Vehicle. ISABE, Bangalore/Indien, 2.-7.9.2001.

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In the frame of JAPHAR project different inlet concepts were designed in order to feed a dual mode ramjet engine propelling a flight test vehicle between Mach 4 and 8 and burning Hydrogen as a fuel. The mixed compression inlets studied by DLR can be operated without bleeding and provide self starting capability at low Mach number, but, due to their high design Mach number (around 6) a large amount of flow spillage occurs at the lowest bound of the flight range. ONERA focused on internal compression inlets requiring bleeding and variable geometry to insure starting, but which could easily be operated with variable geometry to cover a wider Mach number range if necessary. The paper gives the most significant experimental results obtained in H2K (DLR) and S3MA (ONERA) wind tunnels and put the emphasis on CFD validations performed by ONERA on the isolated internal compression inlet.

Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2001,
Title:Inlet Design for Japhar Flight Test Vehicle
AuthorsInstitution or Email of Authors
Volume:ISABE 2001-1136
Event Title:ISABE, Bangalore/Indien, 2.-7.9.2001
Organizer:NAL, Indien
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):UNSPECIFIED
Location: Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Deposited By: elib DLR-Beauftragter
Deposited On:31 Jan 2006
Last Modified:14 Jan 2010 21:04

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