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Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel

Hannemann, Klaus and Martinez Schramm, Jan and Karl, Sebastian and Laurence, Stuart (2015) Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel. 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 06. - 09. July 2015, Glasgow, Scotland, United Kingdom. DOI: 10.2514/6.2015-3608

Full text not available from this repository.

Official URL: http://arc.aiaa.org/doi/abs/10.2514/6.2015-3608

Abstract

The free flight force measurement technique is a very attractive tool to determine forces and moments in particular in short duration ground based test facilities. With test times in the order of a few milliseconds, conventional force balances cannot be applied here. The technique has been applied in a number of shock tunnels utilizing models up to approximately 300 mm in length and looking at external aerodynamics. In the present study the technique is applied using a complex 1.5 m long hypersonic integrated supersonic combustion ramjet (scramjet) engine consisting of intake, combustor and thrust nozzle. For scramjet engines the design objective is a combustor with efficient mixing and combustion within the shortest possible length, but still robust enough to operate in various operational conditions. In the framework of the EU co-funded project LAPCAT II, a M=7.4 scramjet powered small scale flight experiment (SSFE) configuration was designed. Since free jet testing of the complete combustion flow path is a mandatory step within the design roadmap of future engines, ground based testing of the SSFE engine was conducted in the High Enthalpy Shock Tunnel Göttingen (HEG) of the German Aerospace Center, DLR. This type of facility allows duplication of flight conditions in excess of M=8. Here tests were performed simulating Mach 7.4 flight conditions in approximately 28 km altitude. The numerically predicted thrust of the engine could be confirmed in HEG utilizing optical tracking of the free flight wind tunnel model. Combining these experimental results with computed aerodynamic data of the complete SSFE showed that for a selected flight condition a positive aero propulsive balance of the complete configuration could be achieved.

Item URL in elib:https://elib.dlr.de/93538/
Document Type:Conference or Workshop Item (Speech)
Additional Information:AIAA 2015-3608
Title:Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Hannemann, Klausklaus.hannemann (at) dlr.deUNSPECIFIED
Martinez Schramm, Janjan.martinez (at) dlr.deUNSPECIFIED
Karl, Sebastiansebastian.karl (at) dlr.deUNSPECIFIED
Laurence, Stuartstuart.laurence (at) dlr.deUNSPECIFIED
Date:2015
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
DOI :10.2514/6.2015-3608
Page Range:pp. 1-15
Series Name:Conference Proceedings online
Status:Published
Keywords:forces, LAPCAT II, supersonic combustion, high enthalpy
Event Title:20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Event Location:Glasgow, Scotland, United Kingdom
Event Type:international Conference
Event Dates:06. - 09. July 2015
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Anlagen u. Messtechnik
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Micknaus, Ilka
Deposited On:28 Aug 2015 12:03
Last Modified:28 Aug 2015 12:03

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