Surface pressure and heat transfer measurements in the unsteady separated hypersonic flow field over double cones
Reliable bench mark experimental database in the separated hypersonic flow regime is necessary to validate high resolution CFD codes. In this paper we report the surface pressure and heat transfer measurements carried out on double cones (first cone semi-apex angle = 15, 25 deg.; second cone semi-apex angle= 35, 68 deg.) at hypersonic speeds that will be useful for CFD code validation studies. The surface pressure measurements are carried out at nominal Mach number of 8.35 in the IISc hypersonic wind tunnel. On the other hand the surface heat transfer measurements are carried out at a nominal Mach number of 5.75 in the IISc hypersonic shock tunnel. The flow separation point on the first cone, flow reattachment on the second cone and the wild fluctuation of the transmitted shock on the second cone surface (25/68 deg. double cone) in the presence of severe adverse pressure gradient are some of the flow features captured in the measurements. The results from the CFD studies indicate good agreement with experiments in the attached flow regime while considerable differences are noticeable in the separated flow regime.
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- 2.G. Jagadeesh, K.P.J. Reddy, K. Naitou, T. Hashimoto, M. Sun and K. Takayama: Study of separated high enthalpy flow around a double cone. AIAA Paper 2002-0299 (2002)Google Scholar
- 4.G. Jagadeesh: Experimental Investigations of Flow Field Around Large Angle Blunt Cones Flying at Hypersonic Mach Number. Ph.D Thesis, Dept. of Aerospace Engineering, IISc, Bangalore, India (1998)Google Scholar
- 5.M. Sun: Numerical and Experimental Studies of Shock Wave Interaction with Bodies. Ph.D Thesis, Tohoku University, Sendai, Japan (1998)Google Scholar