Limiting Contractions for Starting Prandtl-Meyer-Type Scramjet Inlets with Overboard Spillage

  • N. Moradian
  • E. Timofeev
Conference paper

Introduction

The air inlet is a crucial component of hypersonic airbreathing engines, which should decelerate and compress airflow with minimum losses. For efficient engine operation the inlet must be started, i.e., all incoming supersonic flow must be captured and the flow inside the inlet must be predominantly supersonic. Kantrowitz and Donaldson [1, 2] established the classical theory of flow starting in converging ducts. According to the theory, the limiting duct area ratio for spontaneous starting (or self-starting) is based on the flow condition at which a normal shock is positioned exactly at the duct entry and the post-shock subsonic flow isentropically accelerates along the duct to become sonic at the duct exit (i.e., the choked throat is considered). It is assumed that the flow is quasi-one-dimensional and quasi-steady. For exit-toentry area ratios exceeding the limiting values, which depend on freestream Mach number, the duct (inlet) flow would start on its own, upon the increase of freestream velocity fromzero to the required value. As follows fromthe Kantrowitz theory, limiting contractions for starting lead to low contraction inlets, which do not provide sufficient compression for scramjet operation. Practical, high-contraction inlets do not satisfy the Kantrowitz self-starting condition and would not start spontaneously. This constitutes a well-known inlet starting problem.

Keywords

Mach Number Area Ratio Oblique Shock Freestream Velocity Oblique Shock Wave 
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.
    Kantrowitz, A., Donaldson, C.: Advance Confidential Report L5D20, NACA (1945)Google Scholar
  2. 2.
    Kantrowitz, A.: Technical Note 1225, NACA (1947)Google Scholar
  3. 3.
    Seddon, J., Goldsmith, E.L.: Intake Aerodynamics. AIAA, New York (1985)Google Scholar
  4. 4.
    Evvard, J.C., Blakey, J.W.: NACA, RM E7C26 (1947)Google Scholar
  5. 5.
    Molder, S., Timofeev, E.V., Tahir, R.B.: AIAA Paper 2004-4130 (2004)Google Scholar
  6. 6.
    Koete, J.J., Singh, D.J., Kumar, A., Auslender, A.H.: AIAA JPP 10(6), 841–847 (1994)Google Scholar
  7. 7.
    Smart, M.K., Trexler, C.A.: AIAA JPP 20(2), 288–293 (2004)CrossRefGoogle Scholar
  8. 8.
    Veillard, X., Tahir, R., Timofeev, E., Molder, S.: AIAA JPP 24(5), 1042–1049 (2008)CrossRefGoogle Scholar
  9. 9.
    Tahir, R.B., Molder, S., Timofeev, E.V.: AIAA Paper 2003-5191 (2003)Google Scholar
  10. 10.
    SolverII, Software Package, Ver. 2.30.2385, RBT Consultants, Toronto, ON (2004)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • N. Moradian
    • 1
  • E. Timofeev
    • 1
  1. 1.Department of Mechanical EngineeringMcGill UniversityMontrealCanada

Personalised recommendations