Shock Waves pp 607-612 | Cite as

Experimental investigation of cowl shape and location on inlet characteristics at hypersonic Mach number

  • D. Mahapatra
  • G. Jagadeesh
Conference paper


An experimental study is presented to show the effect of the cowl location and shape on the shock interaction phenomena in the inlet region for a 2D, planar scramjet inlet model. Investigations include schlieren visualization around the cowl region and heat transfer rate measurement inside the inlet chamber.Both regular and Mach reflections are observed when the forebody ramp shock reflects from the cowl plate. Mach stem heights of 3.3 mm and 4.1 mm are measured in 18.5 mm and 22.7 mm high inlet chambers respecively. Increased heat transfer rate is measured at the same location of chamber for cowls of longer lenghs is indicating additional mass flow recovery by the inlet.


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.


  1. 1.
    Michael K. Smart and Carl A. Trexler, AIAA 2003-0012 (2003)Google Scholar
  2. 2.
    D.P. Mrozinski, J.R. Hayes, AiAA 99-0899 (1999)Google Scholar
  3. 3.
    Takeshi Kanda, Tomoyuki Komuro, Goro Masuya, Kenji Kudo, Atsuo Murakami, Kouichiro Tani, Yoshio Wakamatsu and Nobuo Chinzei: Journal of Propulsion and Power 7, 2 (1991)Google Scholar
  4. 4.
    Scott D. Holland, AIAA 92-4026 (1992)Google Scholar
  5. 5.
    S. Boon and R. Hillier, AIAA 2006-12 (2006)Google Scholar
  6. 6.
    Kantrowitz, A and Donaldson, C, duP, ‘Preliminary investigations of supersonic diffusers’, NACA WR L 713, May 1945Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2009

Authors and Affiliations

  • D. Mahapatra
    • 1
  • G. Jagadeesh
    • 1
  1. 1.Aerospace Engineering DepartmentIndian Institute of ScienceIndia

Personalised recommendations