Experimental Investigation of the Flow over an 80

B. Sampath , Rao and Rajan , Kurade Experimental Investigation of the Flow over an 80. In: 51st AIAA Aerospace Sciences Meeting (ASM), Texas, USA, 7-10, January 2013, Texas, USA.

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    The leeward vortex flow over an 80°/45° rounded leading edge double - delta wing – body model with and without control surface deflection at subsonic and transonic speeds and Reynolds number range of 3.64 to 4.36 million has been analyzed for angles of attack ranging from 0 ° to 20° under zero sideslip condition. Details of the flow have been studied using the experimental techniques of force and moment measurements, surface oil flow visualization, continuous schlieren flowfield visualization and realtime surface pressure measurements using differential type of fast response piezoresistive Kulite sensors. The double - delta wing - body model used features a rounded leading edge double - delta wing of an aspect ratio of 2.17 with sweepback angles of 80° at inboard (strake) and 45° at outboard (main wing) with flat bottom and full span control surfaces, fuselage with flat bottom and drooped nose and twin vertical tail. The complex physical phenomena due to interactions among strake vortices, main wing vortices, cross flow and terminating shocks (rear) as visualized from flow visualization and force and moment and real - time pressure data obtained are interrelated and analyzed.Considered are the influence of Mach number and angle of attack on these flow

    Item Type: Conference or Workshop Item (Paper)
    Uncontrolled Keywords: Leading Edge Double delta, Wing body Mode
    Subjects: ENGINEERING > Electronics and Electrical Engineering
    Division/Department: National Trisonic Aerodynamic Facilities, National Trisonic Aerodynamic Facilities
    Depositing User: Ms Indrani V
    Date Deposited: 24 Dec 2013 15:08
    Last Modified: 24 Dec 2013 15:08
    URI: http://nal-ir.nal.res.in/id/eprint/11872

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