Lee Surface Flovv Over Delta Wings at Supersonic Speeds - Some Features of Different Types of Flow

Seshadri, SN and Narayan, KY (1986) Lee Surface Flovv Over Delta Wings at Supersonic Speeds - Some Features of Different Types of Flow. Technical Report. National Aeronautical Laboratory, Bangalore,India.

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    Abstract

    The features of the different types of flow on the lee surface of delta wings at supersonic speeds have been studied in terms of the location of separation and re-attachment lines and shock waves and their variation with Mach number, sweep back, thickness and angle of attack. The study is largely based on tests on two sets flat delta of topped wing models having sweep back angles of 45, 50, 60 and 70 degrees at freestream Mach numbers of 1.6, had 1.8, 2.0, 2.5 and 3.0. The first set of models a wedge angle normal to of 10 the leading edge degrees while the second set had a wedge angle of 25 degrees. In 60 sweepback degree addition, a delta wing with a wedge angle of was 40 degrees also tested. results indicate the that in The leading edge separated flow region, the location of13; attachment and secondary separation lines and their attack depend on the attached location leading the the of the13; shock-induced separation line is independent of the13; particular type of flow. Within each type of flow,13; the effects of thickness are in general found to be13; sma11.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Lee surface flow delta wings;Types of flow
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics, Aerodynamics
    Depositing User: M/S ICAST NAL
    Date Deposited: 19 Sep 2006
    Last Modified: 24 May 2010 09:50
    URI: http://nal-ir.nal.res.in/id/eprint/2738

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