RESEARCH PAPERS: Gas Turbines: Aircraft

Numerical Analysis of Nozzle and Afterbody Flow of Hypersonic Transport Systems

[+] Author and Article Information
T. Esch

Lehrstuhl für Flugantriebe, Technische Universität München, Munich, Federal Republic of Germany

M. Giehrl

Department ETWW, MTU-München GmbH, Munich, Federal Republic of Germany

J. Eng. Gas Turbines Power 117(3), 389-393 (Jul 01, 1995) (5 pages) doi:10.1115/1.2814107 History: Received March 09, 1994; Online November 19, 2007


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.

Copyright © 1995 by The American Society of Mechanical Engineers
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