Shock-Wave Boundary-Layer Interaction Study on a 20' Compression Corner Using PSP and Kulites

Verma, SB and Raju, Channa and Manisankar, C (2011) Shock-Wave Boundary-Layer Interaction Study on a 20' Compression Corner Using PSP and Kulites. Project Report. National Aerospace Laboratories, Bangalore.

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    An experimental unsteadiness in a mechanical vortex 12.56). study was conducted to control the separation shock Mach 2 20' compression ramp-induced interaction using generators (located upstream of interaction at 27.56 and Upstream of the interaction, traces of counter-rotating vortex pairs are clearly indicated by streamwise accumulation of oil pigment. These structures on interaction with the reverse flow in the separation bubble, replace a well-defined separation line (with no control case) by a corrugated separation line. The mean pressure distribution in the interaction region also gets modified and the corresponding rms distributions, in the intermittent region of separation, show a significant reduction in peak rms value. The VG configurations, therefore, help reduce the fluctuations of the separation shock and hence alleviate the fluctuating pressure loads in this region. Within the experimental limitations of transducer pitch and the extent of axial interaction, VG1 configuration seems to be a favorable control in both axial locations and hence seems to be a better flow control VG configuration.

    Item Type: Proj.Doc/Technical Report (Project Report)
    Uncontrolled Keywords: SWBLI, Compression corner, Flow unsteadiness, Vortex generator, Corrugated separation, PSP
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Experimental Aerodynamics Division, Experimental Aerodynamics Division, Experimental Aerodynamics Division
    Depositing User: Smt Bhagya Rekha KA
    Date Deposited: 11 Aug 2011 16:06
    Last Modified: 11 Aug 2011 16:06

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