Advertisement

Journal of Materials Science

, Volume 39, Issue 19, pp 5905–5913 | Cite as

High speed propulsion: Performance advantage of advanced materials

  • T. A. Jackson
  • D. R. Eklund
  • A. J. Fink
Article

Abstract

High-speed air breathing propulsion systems have many attractive military and civil applications. The high propulsive efficiency of these systems allows the exploitation of speed, distance, and bigger payloads, or any combination of the three. The severe operating conditions of these systems require particular attention to overall thermal management of the engine/air-frame. Fuel-cooling the engine structure is a viable way of maintaining thermal balance over a range of flight conditions. Air Force applications have focused on using endothermic hydrocarbon fuels to address this issue because of their compatibility with the military operations. Recent ground tests of scramjet engines have demonstrated adequate performance utilizing state-of-the-art technology in materials. This progress has paved the way for an expendable flight test vehicle in the near future. In order to take full advantage of the capabilities of this propulsion system, advances in fuel-cooled structures, high temperature un-cooled materials, and increased heat capacity of hydrocarbon fuels will be needed to enable expendable systems to reach higher Mach numbers. An additional benefit would be realized in future reusable systems.

Keywords

Mach Number Propulsion System Hydrocarbon Fuel Flight Test High Mach Number 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    R. MERCIER and C. McCLINTON, “Hypersonic Propulsion—transforming the Future of Flight, ” AIAA 2003-2732 (2003).Google Scholar
  2. 2.
    I. M. BLANKSON, Presentation to the U.S.A.F. Scientific Advisory Board (1991).Google Scholar
  3. 3.
    A. C. NIXON, G. H. ACKERMAN, R. D. HAWTHORNE, A. W. RICHIE, H. T. HENDERSON and I. S. BJORKLND, “Vaporization and Endothermic Fuels for Advanced Engine Applications,” AFAPL TDR 64-100 (1964) Parts I, II, and III.Google Scholar
  4. 4.
    A. C. NIXON, G. H. ACKERMAN, L. E. FAITH, R. D. HAWTHORNE, H. T. HENDERSON, A. W. RICHIE, L. B. RYLAND and T. M. SHRYNE, “Vaporization and Endothermic Fuels for Advanced Engine Applications, ” AFAPL TDR 67-114 (1967) Parts I, II, and III.Google Scholar
  5. 5.
    H. HUANG, D. R. SOBEL and L. J. SPADACINNI, “Endothermic Heat-Sink of Hydrocarbon Fuels for Scramjet Cooling, ” 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, AIAA 2002-3871 (2002).Google Scholar
  6. 6.
    K.-C. LIN, P. J. KENNEDY and T. A. JACKSON, “Structures of Internal Flow and the Corresponding Spray for Aerated-Liquid Injectors, ” AIAA 2001-3569 (2001).Google Scholar
  7. 7.
    K.-C. LIN, S. COX-STOUFFER, P. J. KENNEDY and T. A. JACKSON, “Expansion of Supercritical Methane/Ethylene Jets in a Quiescent Subcritical Environment, ” AIAA 2003-0483 (2003).Google Scholar
  8. 8.
    J. A. WHITE and J. H. MORISSON, “Pseudo-Temporal Multi-Grid Relaxation Scheme for Solving the Parabolized Navier-Stokes Equations, ” AIAA Paper 99-3360 (1999).Google Scholar
  9. 9.
    J. R. EDWARDS, Comp. and Fluids 26(6) (1997) 635.Google Scholar
  10. 10.
    T. H. PULLIAM and D. S. CHAUSSEE, J. Comp. Phys. 39 (1981) 347.Google Scholar
  11. 11.
    F. R. MENTER, “Zonal Two Equation k-ω Models for Aerodynamic Flows, ” AIAA Paper 93-2906 (1993).Google Scholar
  12. 12.
    D. C. WILCOX, “Wall Matching, a Rational Alternative to Wall Functions, ” AIAA Paper 89-0611 (1989).Google Scholar

Copyright information

© Kluwer Academic Publishers 2004

Authors and Affiliations

  • T. A. Jackson
    • 1
  • D. R. Eklund
    • 1
  • A. J. Fink
    • 1
  1. 1.Air Force Research LaboratoryWright-Patterson AFBUSA

Personalised recommendations