Aerodynamic drag reduction by heat addition into the shock layer for a large angle blunt cone in hypersonic flow

Reduction in aerodynamic drag for a large angle blunt cone flying at hypersonic Mach number by heat addition into the shock layer is demonstrated in HST2 hypersonic shock tunnel. The heat addition is achieved by the exothermic reaction of chromium atoms ablated from the stagnation region of the chro...

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Bibliographic Details
Published inPhysics of fluids (1994) Vol. 20; no. 8
Main Authors Kulkarni, Vinayak, Hegde, G. M., Jagadeesh, G., Arunan, E., Reddy, K. P. J.
Format Journal Article
LanguageEnglish
Published Melville, NY American Institute of Physics 01.08.2008
Subjects
Aerodynamics
Applied fluid mechanics
Exact sciences and technology
Fluid dynamics
Fundamental areas of phenomenology (including applications)
Physics
Shock waves
Drag reduction
Exothermic reaction
Conical shape
Flow visualization
Aerodynamics
Blunt body
Hypersonic flow
Schlieren method
Experimental study
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Summary:Reduction in aerodynamic drag for a large angle blunt cone flying at hypersonic Mach number by heat addition into the shock layer is demonstrated in HST2 hypersonic shock tunnel. The heat addition is achieved by the exothermic reaction of chromium atoms ablated from the stagnation region of the chromium coated blunt cone with the atomic oxygen behind the shock wave. The measurements show about 47% reduction in the drag coefficient for a 60° apex angle blunt cone in a Mach 8 flow of 3.4 MJ ∕ kg specific enthalpy. The reduction in drag is measured using the accelerometer based force balance system and the heat addition into the shock layer is identified by the surface mounted thin film heat flux gauges and the corresponding movement of the shock wave is visualized by schlieren pictures.
ISSN:1070-6631
1089-7666
DOI:10.1063/1.2944982