The objective of this program was to conduct an experimental and analytical evaluation of low noise exhaust nozzles suitable for future High-Speed Civil Transport (HSCT) aircraft. The experimental portion of the program involved parametric subscale performance model tests of mixer/ejector nozzles in the takeoff mode, and high-speed tests of mixer/ejectors converted to two-dimensional convergent-divergent (2-D/C-D), plug, and single expansion ramp nozzles (SERN) in the cruise mode. Mixer/ejector results show measured static thrust coefficients at secondary flow entrainment levels of 70 percent of primary flow. Results of the high-speed performance tests showed that relatively long, straight-wall, C-D nozzles could meet supersonic cruise thrust coefficient goal of 0.982; but the plug, ramp, and shorter C-D nozzles required isentropic contours to reach the same level of performance. The computational fluid dynamic (CFD) study accurately predicted mixer/ejector pressure distributions and shock locations. Heat transfer studies showed that a combination of insulation and convective cooling was more effective than film cooling for nonafterburning, low-noise nozzles. The thrust augmentation study indicated potential benefits for use of ejector nozzles in the subsonic cruise mode if the ejector inlet contains a sonic throat plane.


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    Titel :

    Generation 1.5 High Speed Civil Transport (HSCT) Exhaust Nozzle Program


    Beteiligte:
    Thayer, E. B. (Autor:in) / Gamble, E. J. (Autor:in) / Guthrie, A. R. (Autor:in) / Kehret, D. F. (Autor:in) / Barber, T. J. (Autor:in) / Hendricks, G. J. (Autor:in) / Nagaraja, K. S. (Autor:in) / Minardi, J. E. (Autor:in)

    Erscheinungsdatum :

    01.11.2004


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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