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Study of the separated high enthalpy flow around a double cone

Jagadeesh, G and Reddy, KPJ and Hashimoto, T and Naitou, K and Sun, M and Takayama, K (2002) Study of the separated high enthalpy flow around a double cone. In: 40th AIAA Aerospace Sciences Meeting & Exhibit, 14-17 January 2002, Reno,NV,U.S.A..

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Official URL: https://doi.org/10.2514/6.2002-299


High enthalpy flow separation over bodies at hypersonic speeds continues to intrigue researchers, since considerable differences are observed between experiments and CFD. In the present study the separated flow field around a double cone has been investigated at nominal stagnation enthalpies of 4.2 MJ/kg and 1.6 MJ/kg. The flow around a double cone (first cone semi-apex angle = 25°; second cone semiapex angle=68°) has been visualized using highspeed image converter camera (IMACON) and double exposure holographic interferometry in the Shock Wave Research Center's (SWRC) free piston driven shock tunnel at Mach 6.99. Presence of a triple shock structure in front of the second cone, and non-linear unsteady shock structure oscillation in the flow field, are the significant results from visualization studies. Further surface convective heat transfer measurements have been carried out at a nominal Mach number of 5.75 in the Indian Institute of Science (USc), hypersonic shock tunnel HST-2. The surface heat transfer in the vicinity of transmitted shock impingement point on the second cone surface fluctuates between 100 W/cm2 - 400 W/cm2 (± 10 ) for nearly identical (± 8 ) free stream conditions, indicating the severe unsteadiness in the flow field. Similar unsteady fluctuations in the heat transfer and oscillatory shock structure in the flow field around the double cone are also observed in the numerical simulations carried out by solving the axi-symmetric Navier-Stokes equations. © 2000 The American Institute of Aeronautics and Astronautics Inc. All rights reserved.

Item Type: Conference Paper
Publication: 40th AIAA Aerospace Sciences Meeting and Exhibit
Publisher: American Institute of Aeronautics and Astronautics Inc.
Additional Information: cited By 2; Conference of 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 ; Conference Date: 14 January 2002 Through 17 January 2002; Conference Code:102855
Keywords: Aerospace engineering; Computational fluid dynamics; Cones; Enthalpy; Flow fields; Flow separation; Heat convection; Holographic interferometry; Navier Stokes equations; Shock waves, Convective heat transfer; Double exposure holographic interferometries; Freestream conditions; Hypersonic speed; Indian institute of science; Stagnation enthalpy; Surface heat transfer; Transmitted shock, Oscillating flow
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 04 Nov 2020 11:15
Last Modified: 04 Nov 2020 11:15
URI: http://eprints.iisc.ac.in/id/eprint/65689

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