Experimental investigation of drag reduction by forward facing high speed gas jet for a large angle blunt cone at Mach 8

Venukumar, Balla and Reddy, KPJ (2007) Experimental investigation of drag reduction by forward facing high speed gas jet for a large angle blunt cone at Mach 8. In: Sadhana: Academy Proceedings in Engineering Sciences, 32 (1-2). pp. 123-131.

Preview

PDF Experimenta.pdf Download (673kB)

Abstract

Substantial aerodynamic drag, while flying at hypersonic Machnumber, due to the presence of strong standing shock wave ahead of a large-angle bluntcone configuration, is a matter of great design concern. Preliminary experimental results for the drag reduction by a forward-facing supersonic air jet for a 60◦ apexangle blunt cone at a flow Mach number of 8 are presented in this paper. The measurements are carried out using an accelerometer-based balance system in the hypersonic shock tunnel HST2 of the Indian Institute of Science, Bangalore. About 29% reduction in the drag coefficient has been observed with the injection of a supersonic gas jet.

Item Type:	Journal Article
Publication:	Sadhana: Academy Proceedings in Engineering Sciences
Publisher:	Indian Academy of Sciences
Additional Information:	Copyright of this article belongs to Indian Academy of Sciences.
Keywords:	Aerodynamic drag;Hypersonic flow;Shock tunnel;Air jet;Force balance;Shock interaction
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	06 Sep 2007
Last Modified:	19 Sep 2010 04:39
URI:	http://eprints.iisc.ac.in/id/eprint/11809

Actions (login required)

View Item