Effect of a supersonic counterflow jet on blunt body heat transfer rates for oncoming high enthalpy flow

被引：13

作者：

Kulkarni V. ^{[1
]}

Reddy K.P.J. ^{[2
]}

机构：

[1] Department of Mechanical Engineering, Indian Institute of Technology Guwahati

[2] Department of Aerospace Engineering, Indian Institute of Science

来源：

Journal of Engineering Physics and Thermophysics | 2009年 / 82卷 / 1期

关键词：

Drag reduction; Free piston shock tunnel; Hypersonic flow;

D O I：

10.1007/s10891-009-0173-1

中图分类号：

学科分类号：

摘要：

Heat transfer reduction studies, in the presence of a supersonic counterflow jet from the stagnation point of a 60-deg apex angle blunt cone, are conducted in a free piston driven hypersonic shock tunnel, HST3, to verify the effectiveness of this technique for high enthalpy flows. For flow of Mach number 8 with stagnation enthalpy of 5 MJ/kg, it has been observed that the heat transfer rate at some location decreases initially with increase in the injection pressure ratio until the critical injection pressure ratio is reached. A forty-five percent reduction in heat transfer rate near the stagnation point has been measured for the critical injection pressure ratio, equal to 14.91. A further increase in the injection pressure ratio reduces the overall percentage heat transfer reduction. The dependence of fluidic spike length on percentage heat transfer reduction has been confirmed. © 2009 Springer Science+Business Media, Inc.

引用

页码：1 / 5

页数：4

共 7 条

[1]

McMahon H.M., An experimental study of the effect of mass injection at the stagnation point of a blunt body, California Institute of Technology Guggenheim Aeronautical Laboratory Hypersonic Research Project Memorandum, 42, (1958)

[2]

Warren C.H.E., An experimental investigation of the effect of ejecting a coolant gas at the nose of a bluff body, J. Fluid Mech., 8, PT. 3, pp. 400-417, (1959)

[3]

Sahoo N., Kulkarni V., Saravanan S., Jagadeesh G., Reddy K.P.J., Film cooling effectiveness on a large angle blunt cone flying at hypersonic speed, Physics of Fluids, 17, 3, (2005)

[4]

Cook W.J., Felderman E.J., Reduction of data from thin film heat transfer gauges: A concise numerical technique, AIAA J., 4, 3, pp. 561-562, (1966)

[5]

Fay J.A., Riddell F.R., Theory of stagnation point heat transfer in dissociated air, J. Aeronaut. Sci., 25, pp. 73-85, (1958)

[6]

Lee L., Laminar heat transfer rate over blunt nosed body at hypersonic speeds, Jet Propulsion, 26, pp. 259-269, (1956)

[7]

Venukumar B., Jagadeesh G., Reddy K.P.J., Counterflow drag reduction by supersonic jet for a blunt body in hypersonic flow, Phys. Fluids, 18, 11, pp. 1-4, (2006)

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