Analysis of High Mach 2DCD and SERN Scale Model Test Data PUBLIC ACCESS

[+] Author Affiliations
G. E. Hoff, R. W. Whittaker

General Electric – Aircraft Engines, Cincinnati, OH

Paper No. 93-GT-429, pp. V03CT17A090; 6 pages
  • ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3C: General
  • Cincinnati, Ohio, USA, May 24–27, 1993
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7892-7
  • Copyright © 1993 by ASME


This paper presents the results of analysis of scale model cold flow static performance test data for 2DCD and SERN High Mach (4 to 6) nozzle configurations generated under a GE Aircraft Engines Independent Research and Development Program. The testing was conducted at FluiDyne Engineering Corporation in late 1989. For the 2DCD nozzles, throat area, divergent flap length, contour, expansion ratio, and nozzle pressure ratio were parametrically varied and simulated operating conditions from subsonic to Mach 6. SERN nozzle parameters varied included throat area, expansion ramp length, cowl length and cowl divergence angle. Geometrics and nozzle pressure ratios simulated subsonic to Mach 6 operation. Although these tests were conducted statically, i.e., external flow was not simulated, the analysis presented herein addresses design point performance where the internal performance is not expected to be significantly influenced by external flow.

Data from the test program have been examined for comparison with existing GE performance prediction methods. A second objective was to explore generalization of the data for the preparation of prediction methodologies and design guides for future High Mach propulsion system studies. In general, the study results presented in this paper indicate that current GE 2DCD prediction methods do not extrapolate to the High Mach nozzle regime. Also presented are general performance trends as a function of key geometric parameters and potential correlating factors which provide guidelines for the design of future High Mach exhaust systems.

Copyright © 1993 by ASME
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