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Flow control by energy deposition in hypersonic flow - some fundamental considerations

Banuti, Daniel and Hannemann, Klaus (2010) Flow control by energy deposition in hypersonic flow - some fundamental considerations. Conference Proceedings. 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, 19. - 22. Oct. 2009, Bremen, Germany. ISBN 978-1-60086-740-8.

Full text not available from this repository.

Official URL: http://www.aiaa.org

Abstract

This paper discusses some general properties of energy deposition in hypersonics. Extending the flight envelope of passenger aircraft to high Mach numbers comes with problems unsolved before in civil flight, such as sonic boom, or excessive thermal and mechanical loads. Energy deposition is regarded as a possible remedy to a multitude of problems occurring in this flight regime and thus studied here. A new energy source term has been implemented into the DLR TAU CFD code which models a physical distributed heat addition. In a first step, energy deposition in free flow is investigated using this new term. Four flow topologies, dependent on the deposition energy, have been identified, ranging from negligible induced cross flow component, to a massive detached bow shock ahead of the deposition region. In a second step, ramp flow, as a precursor to flow about an airfoil, is studied under the influence of an upstream energy deposition region. An undesired low pressure region could be explained with a simplified model of wave refraction at thermally stratified ramp flow. Key of this model is a flow deflection above the ramp which is needed to balance pressure differences. This model is discussed in detail to fully understand the physical nature of the flow structure. It predicts a way of increasing surface pressure compared to regular ramp flow at reduced total pressure loss. It furthermore predicts the occurrence of premature shock separation and oscillating shock patterns. Analyzing this model, a simple yet accurate functional formula is found for the additional deflection angle due to refraction which simplifies the calculation of the surface pressure distribution as no pressure balance iteration is needed anymore. These studies are currently carried out within the European ATLLAS project which is concerned with the development of hypersonic passenger aircraft. Computations are performed using the DLR TAU code, a finite volume, second order accuracy, compressible flow solver.

Document Type:Conference or Workshop Item (Speech, Paper)
Title:Flow control by energy deposition in hypersonic flow - some fundamental considerations
Authors:
AuthorsInstitution or Email of Authors
Banuti, DanielUNSPECIFIED
Hannemann, KlausUNSPECIFIED
Date:2010
Refereed publication:No
In SCOPUS:No
In ISI Web of Science:No
Volume:Vol. 14
Publisher:Conference Proceedings
Series Name:2009 AIAA Meeting Papers on Disc. (DVD-ROM)
ISBN:978-1-60086-740-8
Status:Published
Keywords:hypersonics shock refraction
Event Title:16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
Event Location:Bremen, Germany
Event Type:international Conference
Event Dates:19. - 22. Oct. 2009
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):W - Raumfahrzeugsysteme - Numerische Verfahren und Simulation (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Daniel Banuti
Deposited On:03 Dec 2010 08:19
Last Modified:03 Dec 2010 08:19

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