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.

Full text available as:
[img] PDF
Restricted to Registered users only

Download (1794Kb) | Request a copy

    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: Proj.Doc/Technical Report (Project Report)
    Uncontrolled Keywords: Shock boundary layer interaction, Swept shock interaction, Blunt fin shock interaction
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Experimental Aerodynamics Division, Experimental Aerodynamics Division, Experimental Aerodynamics Division, Other
    Depositing User: Smt Bhagya Rekha KA
    Date Deposited: 26 Mar 2012 16:07
    Last Modified: 26 Mar 2012 16:07
    URI: http://nal-ir.nal.res.in/id/eprint/10405

    Actions (login required)

    View Item