Simulation of a SERN/Afterbody Flow Field regarding heated Nozzle Flow in the Hypersonic Facility H2K
Gruhn, P. and Henckels, A. (2002) Simulation of a SERN/Afterbody Flow Field regarding heated Nozzle Flow in the Hypersonic Facility H2K. In: Notes on Numerical Fluid Mechanics and Multidisciplinary Design New Results in Numerical and Experimental Fluid Mechanics IV, 87. Springer-Verlag. ISBN 3-540-20258-7.
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An experimental study with respect to the influence of temperature changes on the interaction of a SERN nozzle flow with the external flow around a nozzle model has been performed in the hypersonic wind tunnel H2K. The static pressure along the expansion ramp and the nozzle flap was measured at varying total temperatures of the nozzle flow between 300 K and 1000 K. Additional information about the flow was gained by Schlieren optics. It was found that the axial thrust was increased by up to 1.5 per cent with increasing air temperature. Considering the impact of the nozzle thrust on the net thrust of airbreathing engines at hypersonic speeds, this demonstrates the importance of simulating the "hot" nozzle flow for the investigation of interacting nozzle flow fields.
|Document Type:||Contribution to a Collection|
|Title:||Simulation of a SERN/Afterbody Flow Field regarding heated Nozzle Flow in the Hypersonic Facility H2K|
|Journal or Publication Title:||Notes on Numerical Fluid Mechanics and Multidisciplinary Design|
|In ISI Web of Science:||No|
|Series Name:||New Results in Numerical and Experimental Fluid Mechanics IV|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Space|
|HGF - Program Themes:||W RP - Raumtransport|
|DLR - Research area:||Space|
|DLR - Program:||W RP - Raumtransport|
|DLR - Research theme (Project):||UNSPECIFIED|
|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 21:05|
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