Study of glancing and blunt fin shock-boundary layer interactions at low supersonic mach numbers

Mukund, R and Viswanath, PR and Prabhu, A and Vasudevan, B (2003) Study of glancing and blunt fin shock-boundary layer interactions at low supersonic mach numbers. Project Report. National Aerospace Laboratories, Bangalore.

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Abstract

Experiments have been carried out investigating both sharp fin and blunt fin-induced turbulent boundary layer interactions at freestream Mach numbers of-1 .80 and 2 .47. Two sharp fin models of wedge angle 10° and 15° and three blunt fin models of different nose diameter were chosen for this study . Surface pressure distributions were measured and surface flow visualization studies were carried out for all the cases . The results show that the interactions at these relatively lower freestream Mach numbers are broadly similar to those observed at higher Mach numbers (> 3.0). It is suggested that the influence of the blunt nose exists atleast upto 3d in the spanwise or lateral direction.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Shock boundary layer interaction, Swept shock interaction, Blunt fin shock interaction
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Smt Bhagya Rekha KA
Date Deposited: 26 Mar 2012 10:37
Last Modified: 26 Mar 2012 10:37
URI: http://nal-ir.nal.res.in/id/eprint/10405

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