Using an implicit Finite-Volume Navier–Stokes code, the flow field in a Single Expansion Ramp Nozzle (SERN) for a hypersonic aircraft is studied. Comparisons between experimental data and CFD calculations for certain components of the integrated exhaust system (cold two-dimensional nozzle flow, high temperature reacting three-dimensional combustion chamber flow, and two-dimensional nozzle flow with external flow) are presented. To show the sensitivity of the considered components to off-design operating conditions, comprehensive numerical studies have been carried out. For the determination of nozzle performance a detailed two-dimensional analysis from transonic to hypersonic flight Mach numbers has been performed. A direct optimization method has been used to investigate the influence of the lower nozzle flap shape on the thrust vector.
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July 1995
Research Papers
Numerical Analysis of Nozzle and Afterbody Flow of Hypersonic Transport Systems
T. Esch
Lehrstuhl fu¨r Flugantriebe, Technische Universita¨t Mu¨nchen, Munich, Federal Republic of Germany
M. Giehrl
Department ETWW, MTU-Mu¨nchen GmbH, Munich, Federal Republic of Germany
J. Eng. Gas Turbines Power. Jul 1995, 117(3): 389-393 (5 pages)
Published Online: July 1, 1995
Article history
Received:
March 9, 1994
Online:
November 19, 2007
Citation
Esch, T., and Giehrl, M. (July 1, 1995). "Numerical Analysis of Nozzle and Afterbody Flow of Hypersonic Transport Systems." ASME. J. Eng. Gas Turbines Power. July 1995; 117(3): 389–393. https://doi.org/10.1115/1.2814107
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