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Design of a Scramjet Nozzle with Streamline Tracing Technique and Reference Temperature Methode

Riehmer, Johannes und Gülhan, Ali (2011) Design of a Scramjet Nozzle with Streamline Tracing Technique and Reference Temperature Methode. 7th Aerothermodynamics Symposium on Space Vehicles 2011, 9-12 May 2011, Brügge, Belgien.

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This study presents a method to find an optimal shape of a three-dimensional supersonic nozzle for a rectangular scramjet combustion chamber with rounded edges by taking into account the skin friction effects. The geometric and flow constraints are defined within the German DFG GRK 1095/2 project and the designed nozzle will be part of a scramjet demonstrator configuration. The nozzle inlet conditions are mean values of the combustion chamber exit conditions with the assumption of a constant specific heat ratio. To generate the shape of the nozzle a streamline tracing technique is applied to an axis-symmetric flow field calculated by the Method of Characteristics (MOC). Skin friction in relatively high pressure supersonic flow from the combustion chamber is very dominant and cannot be neglected in the design process. Therefore the skin friction is calculated using the Reference Temperature Method (RTM) and used for the determination of the thrust and moment vectors. This allows considering viscous effects without boundary layer calculations. With this approach an optimal truncated ideal nozzle contour which yields the geometric constraints can be derived. For the validation of this method comparative calculations have been carried out with the DLR code TAU on an exemplary axis-symmetric supersonic nozzle for different flow conditions. Results showed a good agreement. Finally for the three-dimensional nozzle the analytical solution for the inviscous and viscous case provided comparable data like TAU simulations. Further simplifications of the approach for an efficient three-dimensional nozzle design will be addressed in the paper.

Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Design of a Scramjet Nozzle with Streamline Tracing Technique and Reference Temperature Methode
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID
Riehmer, Johannesjohannes.riehmer@dlr.deNICHT SPEZIFIZIERT
Gülhan, Aliali.guelhan@dlr.deNICHT SPEZIFIZIERT
Datum:2 Mai 2011
Referierte Publikation:Nein
In Open Access:Nein
In ISI Web of Science:Nein
Stichwörter:Scramjet, Reference Temperature Method, Method of Characteristics
Veranstaltungstitel:7th Aerothermodynamics Symposium on Space Vehicles 2011
Veranstaltungsort:Brügge, Belgien
Veranstaltungsart:internationale Konferenz
Veranstaltungsdatum:9-12 May 2011
Veranstalter :European Space Agency
HGF - Forschungsbereich:Verkehr und Weltraum (alt)
HGF - Programm:Weltraum (alt)
HGF - Programmthema:W RP - Raumtransport
DLR - Schwerpunkt:Weltraum
DLR - Forschungsgebiet:W RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):W - Zukünftige Raumtransporter - Entwurf und Simulationsmethoden für Raumtransporter (alt)
Standort: Köln-Porz
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Über- und Hyperschalltechnologien
Hinterlegt von: Riehmer, Johannes
Hinterlegt am:25 Mai 2011 07:37
Letzte Änderung:26 Okt 2015 08:19

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